Documentation(1) 2 2

OPTIMISATION OF STEAM TURBINE BLADE MATERIAL amp ITS ANALYSIS

A project report submitted to

Jawaharlal Nehru Technological University

Kakinada in the partial fulfillment for the award of

Degree of BACHELOR

OF TECHNOLOGY

MECHANICAL ENGINEERING

Submitted by

VSURENDRA KUMAR

GCALEB PAUL ARAHUL

MLOKESH GSIVA

Under the esteemed guidance of

MrKCHANDRA SEKHARAsso Professor

BATCH 2009-13 DEPARTMENT OF MECHANICAL ENGINEERING

QISCOLLEGE OF ENGINEERING amp TECHNOLOGY

An ISO Certified amp accredited by NBA institute (Affiliated to JawaharlalNehruTechnologicalUniversity Kakinada)

ONGOLE ndash 523 272 AP

VENGAMUKKA PALEM ndash 523272 AP

DEPARTMENT OF MECHANICAL ENGINEERINGCERTIFICATE

This is to certify that the project entitled

ldquoOPTIMIZATION OF STEAM TURBINE BLADE MATERIAL amp ITS

ANALYSISrdquois a bonafied work of the following final BTech studentsin

the partial fulfillment of the requirement for the award of the degree of

Bachelor of Technology inMECHANICAL ENGINEERING

for the academic year 2009-13

VSURENDRA KUMAR

GCALEB PAUL ARAHUL

MLOKESH GSIVA

Signature of guide Signature of Head of DepartmentMrKCHANDRASEKHAR Dr BSRMURTHY MTech( PhD) MTechPhD

Signature of Principal Signature of External Examiner DrKVEERASWAMY ME PhD

DECLARATION

We do here by declare that the project report entitled

ldquoOPTIMISATION OF STEAM TURBINE BLADE

MATERIAL amp ITS ANALYSISrdquo is an original work done and

submitted by us as a partial fulfillment for the award of degree of

Bachelor of Technology

VSURENDRA KUMARGCALEB PAUL

ARAHULMLOKESH

ACKNOWLEDGEMENT

We thank the almighty for giving us the courage and perseverance in completing

the project This is itself an acknowledgement for all those people who have given us

their heartfelt cooperation in making this project a grand success

It is great pleasure to express our deep and sincere gratitude to the project guide

SriKCHANDRA SEKHAR MTech(PhD) Associate professor for extending their

sincere and heart full guidance throughout the project work

We are greatly debated to our Head of the deptDrBVSMURTHY MTECH

PhDfor giving valuable guidance at every stage of the project work We are profoundly

grateful towards the unmatched services rendered by himWe are thankful to our

principal DrKVEERASWAMY ME PhD MISTE for giving us the opportunity for doing

this project at an esteemed organization

Our special thanks to all lectures of Mechanical Engineering department for their

valuable advices at every stage of this work Without their supervision and many hours of

devoted guidance stimulating and constructive criticism and this thesis would never

have come out in this form

We would like to thank our friends whose direct or indirect help has enabled us to

complete this work successfully

Last but not least we would like to express our deep sense of gratitude to our

beloved parents for their moral support

ARAHULMLOKESH

ABSTRACT

A steam turbine is a mechanical device that extracts thermal energy from pressurized

steam and converts it into rotary motion A system of angled and shaped blades arranged

on a rotor through which steam is passed to generate rotational energy

The blades are designed in such a way as to produce maximum rotational energy by

directing the flow of the steam along its surface The blades are made at specific angles in

order to incorporate the net flow of steam over it in its favor The blades may be of

stationary or fixed and rotary or moving or types

The main aim of the project is to suggest the best material with in low cost The

project equipped with the construction and analysis of steam turbine blade with different

materials used generally (chrome steel titanium) and the project improves the mechanical

properties like stress displacement temperature gradient and thermal flux etc of

bladematerial for which the new material usage is introduced which is cast iron with

zirconium coating

The theme of the project is to design a steam turbine blade using 3D modeling

software ProEngineer by using the CMM point data

In this project we are conducting structural and modal analysis by applying the

pressures By conducting above analysis we are finding stresses developing on blade and

mode shape of the blade In our project we are also conducting thermal analysis for

finding temperature distributing on blade

ProENGINEER is the standard in 3D product design featuring industry-leading

productivity tools that promote best practices in design

Thermal analysis to verify the thermal characteristics of the blade is also done by

applying temperatures Structural and thermal analyses are done in ANSYS

ANSYS is general-purpose finite element analysis (FEA) software package Finite

Element Analysis is a numerical method of deconstructing a complex system into very

small pieces (of user-designated size) called elements

CONTENTS-

CHAPTER-1 INTRODUCTIONTO STEAM TURBINE BLADE

11 INTRODUCTION

12 MANFACTURING OF STEAM TURBINE BLADE

13 OPTIMIZATION TECHNIQUES AND SELECTION

CHAPTER-2 INTRODUCTION TO NEW BLADE MATERIAL

CONCEPT

21 MATERIALS USED TO MANFACTURE STEAM TURBINE BLADE

22 NEW BLADE MATERIAL INTRODUCTION AND ITS PROPERTIES

CHAPTER-3 DESIGN OVERVIEW

31CMM DATA

311GENERATION OF PRESSURE DISTRIBUTION ON TURBINE BLADE

32 LAYER OVERVIEW

33 INTRODUCTION TO CAD

34INTRODUCTION TO PRO-E

35DESIGN OF BLADE

351 DESIGN CONSIDERATIONS

352 DESIGN PROCEDURE

CHAPTER-4 ANALYSIS OF STEAM TURBINE BLADE

41INTRODUCTION TO ANSYS

42 ANALYSIS OF BLADES WITH DIFFERENT MATERIALS

CHAPTER-5 RESULTS OF ANALYSIS ON BLADE

CHAPTER-6 CONCLUSION

CHAPTER-7 BIBLIOGRAPHY

CHAPTER-1INTRODUCTION

TO STEAM TURBINEBLADE

11 INTRODUCTION

STEAM TURBINE-

A steam turbine is a mechanical device that extracts thermal energy

from pressurized steam and converts it into rotary motion A system of angled and

shaped blades arranged on a rotor through which steam is passed to generate rotational

energy and this energy is used for generation of power

BLADE-

The blade is one of the crucial part of the Entire turbine construction if the profile is vary

a little bit its entire system efficiency will effects not only blade profile but also the

material used

The blades are of two types Which is stationary blades moving bladesThe stationary

blades are used like nozzles for converting pressure energy into kinetic energy Generally

these are fixed on frame where as the other type of blades are (moving blades) fixed on

rotor these will absorbs energy which is generated from fixed blades This is the

mechanism occurred in the reaction turbine

But where as in impulse turbine the steam (jet) will directly touches the

blade profile here we are going to use of fixed blades In those two types each having

their special features advantages amp disadvantages

The blades are manufactured by using various machining process amp various tools

based on work material (work piece) optimization of tool usage Of course it is a costly

process amp takes more time for reducing both cost amp time we are going to do this project

Not only that but also we can reduce monthly maintenance like replacement turbine

blades

Generally now a dayrsquos titanium is used as blade material but it is a costly one

so with good properties which are required for blade here our project deals with

optimization of materials with the replacement of titanium with low cost material by use

of refectories It is used like a painting on surface

12 MANUFACTURING OF STEAM TURBINE BLADE

The different processes followed in the manufacture of steam turbine blade on CNC 3axis

machine as follows

1 RAW MATERIAL PROCUREMENTThe steam turbine blade material is procured as

per the design specification The material is inspected dimensionally and all the

mechanical and chemical analysis are made as per the specification

2 LENGTH CUTTING

The material is cut to length by keeping machining allowance at both ends either by Band

Saw or by Power Hack Saw

3 THICKNESS MILLING

The material is clamped in a vice or fixture and thickness is milled on both sides by

keeping n allowance of 05mm on both sides for grinding This operation is done either

by horizontal milling machining or by vertical milling machine

4 THICKNESS GRINDINGThe milled bars are deburred and kept on a magnetic chuck

of the segmental surface grinding machine 5 to 10 blades are kept each time depending

on the size and ground each side to maintain the dimension The tolerance on the grinding

dimensions would be +‐005 mm and parallarith should be within 002 mm

5 RHOMBOID MILLINGThe ground blade bars are milled to rhomboid shape with an

angle given in the process by clamping in a fixture on both sides with an allowance of

05mm on both side This is done on the horizontal milling machines

6 RHOMBOID GRINDING

The milled bars are deburred and kept on magnetic chuck of the surface grinder and

grinding is done on both sides and the tolerance should be +‐005 mm The surface must

be within 8 microns

7 FACING AND SIZE MILLING

The ground blades are faced on the root side to maintain perpendicularity This is very

important as the blade is held on this face while in assembly Then on other side size

milling is done to maintain the total length of blades as per the drawing

8 ROOT MILLINGClamp the blade in a vice or ficture and machine the root on both

sides as per drawing keeping an allowance for root radius Do not machine 2 blade as

these are used for locking purpose This operation is done on horizontal milling machine

9 ROOT RADIUS MILLING

Clamp the blade in a vice or fixture and machine the root radius as per drawing by CNC

Machining centre This operation is done on CNC Vertical machining centre by CNC

Program

10 WIDTH MILLINGThe profile width is done on both sides on horizontal milling

machine as per the drawing

11 CONVEX MILLINGThe milling is done on convex side by aCNC machining centre

The CNC Program is developed based on the profile coordinates and then loaded into the

CNC system of the machine

12 CONCAVE MILLING

The profile milling is done on concave side by a CNC machining center The CNC

Program is developed based on the profile coordinate and then loaded in to the CNC

system of the machine

13 TAPER MILLING

The taper milling is done on a horizontal milling machine by putting in a fixture specially made The taper is calculated

Etc are the steps in manufacturing

Optimization techniques can be classified based on the type of constraints nature of

design variables physical structure of the problem nature of the equations involved

deterministic nature of the variables permissible value of the design variables

separability of the functionsand number of objective functions

Classification based on the nature of the design variables

1048698There are two broad categories of classification within this classification

1048698First category the objective is to find a set of design parameters that make a prescribed function of these parameters minimum or maximum subject to certain constraints

1048698Second category the objective is to find a set of design parameters which are all continuous functions of some other parameter that minimizes an objective function subject to a set of constraints

Classification based on the physical structure of the problem

1048698Based on the physical structure we can classify optimization problems are classified as optimal controland non-optimal controlproblems

(i)Anoptimal control (OC)problem is a mathematical programming problem involving a number of stages where each stage evolves from the preceding stage in a prescribed manner

1048698It is defined by two types of variables the control or design variables and state variables(ii) The problems which are not optimal control problemsarecalled non-optimal control problems

Classification based on the nature of the equations involved

1048698Based on the nature of expressions for the objective function and the constraints optimization problems can be classified as linear nonlinear geometric and quadratic programming problems

(i)Linear programming problem1048698If the objective function and all the constraints are linear functions of the design variables the mathematical programming problem is called a linear programming (LP) problem

(ii) Nonlinear programming problem1048698If any of the functions among the objectives and constraint functions is nonlinear the problem is called a nonlinear programming (NLP) problem this is the most general form of a programming problem

(iii)Geometric programming problemndashA geometric programming (GMP) problem is one in which the objective function and constraints are expressed as polynomials in X

(iv) Quadratic programming problem1048698A quadratic programming problem is the best behaved nonlinear programming problem with a quadratic objective function and linear constraints and is concave (for maximization problems)

Classification based on the permissible values of the decision variables

1048698Under this classification problems can be classified asintegerand real-valuedprogramming problems

(i) Integer programming problem1048698If some or all of the design variables of an optimization problem are restricted to take only integer (or discrete) values the problem is called an integer programming problem

(ii) Real-valued programming problem1048698A real-valued problem is that in which it is sought to minimize or maximize a real function by systematically choosing the values of real variables from within an allowed set When the allowed set contains only real values it is called a real-valued programming problem

1048698Under this classification optimization problems can be classified as deterministicandstochastic programming problems

(i) Deterministic programming problem

bullIn this type of problems all the design variables are deterministic

(ii) Stochastic programming problem1048698In this type of an optimization problem some or all the parameters (design variables andor pre-assigned parameters) are probabilistic (non deterministic or stochastic) For example estimates of life span of structures which have probabilistic inputs of the concrete strength and load capacity A deterministic value of the life-span is non-attainable

Classification based on the number of objective functions

1048698Under this classification objective functions can be classified as singleand

multiobjectiveprogramming problems

(i)Single-objective programming problemin which there is only a single objective

(ii) Multi-objective programming problem

Optimization Technique Selection Criteria

We have selected the optimization of design variable of material selection criteria

where it can give good results in optimization analysis This technique comes under the

category of optimization under based upon design variables

In the project the total description contains not only optimization and the

comparison of the new material with generally used materials The individual analysis

also done in the total project

CHAPTER-2INTRODUCTIONTO NEW BLADE

DESIGN

21 MATERIALS USED TO MANFACTURE STEAM TURBINE

The type of material used for turbine blades is based on the stage of the turbine in

which the blades will operate There are three such stages high-pressure (HP)

intermediate-pressure (IP) and low-pressure (LP) which are named according to the

relative pressure of the steam in the stage The pressures and temperatures of each stage

limit the kinds of materials that may be used in them For instance HP and IP stage

blades are generally made from 12Cr martesitic stainless steels However blades used in

high-temperature (gt 450 C) HP or IP applications may be made of austenitic stainless

steels because they have better mechanical properties at high temperatures For example

stainless steel type AISI 422 (a martensitic stainless steel) is commonly used for HP and

IP turbine sections while AISI series 300 steels (austenitic) are used for high-temperature

applications LP blades are often but not exclusively made from 12Cr stainless steels

also Common types of stainless steel used in LP sections include AISI types 403 410

410-Cb and 630 the exact type of steel chosen for a particular LP application depends

on the strength and corrosion resistance required

Since the 1960s titanium alloys especially Ti-6Al-4V have also been used for

LP turbine stages These alloys are particularly suited to LP stages for a number of

reasons First the densities of titanium alloys are generally less than the density of steels

for example Ti-6Al-4V has a density of only 443 gcc while stainless steel type AISI

410S has a density of 78 gcc This lower density makes it possible to lengthen the LP

blades and thereby increase turbine efficiency without increasing stresses in the blades

due to centrifugal forces Second titanium alloys have greater corrosion resistance than

steels this makes titanium alloys ideal for use in LP stages where there are greater levels

of moisture Finally titanium alloys are resistant enough to water droplet erosion that

they can be used without erosion protection in certain applications

Overall it is the material properties that make a blade reliable or doomed to

failure The yield strength tensile strength corrosion resistance and modulus of

elasticity all play a role in determining whether or not a blade will fail under operating

22 NEW BLADE MATERIAL INTRODUCTION AND ITS

PROPERTIES

Generally the blade will be manufactured with stainless steel chrome steel and

some other alloy steels If the higher performance and higher efficiency is needed the

blades are manufactured with titanium which is high in cost and have good properties

Due to high cost it is very difficult to maintain and the initial investment will be high So

a material need is came in front to minimize cost and to proportionate the good properties

in it We selected cast iron with zirconium coating which will give the better properties

than the titanium material The properties of the material are listed below

Cast Iron

Material Metal Ferrous Metal Cast Iron

Material Notes This property data is a summary of similar materials in the MatWeb database for the category Cast Iron Each property range of values reported is minimum and maximum values of appropriate MatWeb entries The comments report the average value and number of data points used to calculate the average The values are not necessarily typical of any specific grade especially less common values and those that can be most affected by additives or processing methods

Physical Properties

Metric English Comments

Density 554 - 781 gcc

0200 - 0282

lbinAcircsup3

Average value 724 gcc Grade Count69

Mechanical Properties

Hardness Brinell

120 - 807 120 - 807 Average value 300 Grade Count134

Hardness Knoop

Hardness Rockwell B

Hardness Rockwell C

Hardness Vickers

Tensile Strength Ultimate

118 - 1650 MPa

17100 - 240000 psi

Average value 516 MPa Grade Count137

Tensile Strength Yield

655 - 1450 MPa

9500 - 210000 psi

Elongation at Break

100 - 250 100 - 250

Average value 828 Grade Count93

Reduction of Area

200 - 100 200 - 100

Modulus of Elasticity

621 - 240 GPa 9000 - 34800 ksi

Average value 147 GPa Grade Count62

Flexural Yield Strength

248 - 655 MPa 36000 - 95000 psi

Compressive Yield Strength

331 - 2520 MPa

48000 - 365000 psi

Poissons Ratio

0240 - 0370 0240 - 0370

Fatigue Strength

689 - 510 MPa

10000 - 74000 psi

Fracture Toughness

440 - 109 MPa-mAcircfrac12

400 - 992 ksi-inAcircfrac12

Average value 700 MPa-mAcircfrac12 Grade Count5

Machinability

0000 - 125 0000 - 125

Shear Modulus

270 - 676 GPa

3920 - 9800 ksi

Shear Strength

149 - 1480 MPa

21600 - 215000 psi

Izod Impact Unnotched

400 - 244 J 295 - 180 ft-lb

Average value 655 J Grade Count12

Charpy 678 - 271 J 500 - 200 Average value 129 J Grade Count9

Impact ft-lbCharpy Impact Unnotched

407 - 123 J 300 - 910 ft-lb

Electrical Properties

Electrical Resistivity

000000500 - 110 ohm-cm

000000500 - 110

ohm-cm

Average value 611 ohm-cm Grade Count18

Magnetic Permeability

Thermal

PropertiesMetric English Comments

CTE linear 775 - 193 Acircmicromm-AcircdegC

431 - 107 Acircmicroinin-

AcircdegF

Average value 127 Acircmicromm-AcircdegC Grade Count29

Specific Heat Capacity

0506 Jg-AcircdegC 0121 BTUlb-

AcircdegF

Average value 0506 Jg-AcircdegC Grade Count6

Thermal Conductivity

113 - 533 Wm-K

784 - 370 BTU-inhr-

ftAcircsup2-AcircdegF

Average value 252 Wm-K Grade Count23

Melting Point

1120 - 2220 AcircdegC

2050 - 4030 AcircdegF

Average value 1210 AcircdegC Grade Count8

Maximum Service Temperature Air

649 - 982 AcircdegC 1200 - 1800 AcircdegF

Minimum Service Temperature Air

-594 - -300 AcircdegC

-750 - -220 AcircdegF

Average value -349 AcircdegC Grade Count6

Shrinkage 0800 - 150 0800 - 150

Zirconium Zr

Material Metal Nonferrous Metal Zirconium Alloy Pure Element

Material Notes This entry is for pure Zr MatWeb also has data sheets for many Zr alloys

Characteristics

DuctileMechanical Properties similar to titanium and austenitic stainless steelExcellent corrosion resistanceTransparent to thermal energy neutronsForms adherent refractory double-oxide layer above 650AcircdegCHighly anisotropic undergoes allotropic transormation from hcp-structured alpha phase to bcc-structured beta phase at 870AcircdegC

Applications

SuperalloysAlloying with Aluminium Copper Magnesium or Titanium

Water-cooled Nuclear reactorsChemical processing equipment

Physical

Density 653 gcc 0236 lbinAcircsup3 Vapor Pressure 1013e-10 bar 7598e-8 torr

Temperature 1574 AcircdegC Temperature 2865 AcircdegF

1013e-9 bar 7598e-7 torr Temperature 1690 AcircdegC Temperature

3070 AcircdegF 1013e-8 bar 0000007598 torr

1013e-7 bar 000007598 torr Temperature 1976 AcircdegC Temperature

3589 AcircdegF 0000001013 bar 00007598 torr

000001013 bar 0007598 torr Temperature 2367 AcircdegC Temperature

Chemical Properties

Atomic Number 40 40 Thermal Neutron Cross Section

018 barnsatom 018 barnsatom

X-ray Absorption Edge

068877 Atildehellip 068877 Atildehellip K

48938 Atildehellip 48938 Atildehellip LI

537088 Atildehellip 537088 Atildehellip LII

557374 Atildehellip 557374 Atildehellip LIII

Electronegativity 133 133 PaulingIonic Radius 0790 Atildehellip 0790 Atildehellip Crystal Ionic

Radius for Valence +4

109 Atildehellip 109 Atildehellip Crystal Ionic Radius for

Valence +1Electrochemical 0844 gAh 0844 gAh

Equivalent

Hardness Brinell 145 145 Converted from Vickers for 3000

kg load10 mm ball Annealed

sampleHardness Rockwell A

49 49 Converted from Vickers

annealed sampleHardness Rockwell B

Annealed sampleHardness Vickers 150 150 annealed sampleTensile Strength Ultimate

330 MPa 47900 psi Annealed

Elongation at Break 32 32 AnnealedModulus of Elasticity

945 GPa 13700 ksi

Poissons Ratio 034 034 Shear Modulus 353 GPa 5120 ksi Calculated

00000400 ohm-cm 00000400 ohm-cm

Magnetic Susceptibility

000000134 000000134 cgsg

Critical Magnetic Field Strength Oersted

Critical Superconducting Temperature

0610 K 0610 K Acircplusmn015 065 095 K for omega Zr

Thermal Properties

Heat of Fusion 251 Jg 108 BTUlb CTE linear 580 Acircmicromm-AcircdegC 322 Acircmicroinin-AcircdegF

Temperature 200 - 100 AcircdegC

Temperature 680 - 212 AcircdegF

630 Acircmicromm-AcircdegC 350 Acircmicroinin-AcircdegF Temperature 250 AcircdegC Temperature

482 AcircdegF 690 Acircmicromm-AcircdegC 383 Acircmicroinin-AcircdegF

0285 Jg-AcircdegC 00681 BTUlb-AcircdegF

167 Wm-K 116 BTU-inhr-ftAcircsup2-AcircdegF

Melting Point 1852 AcircdegC 3366 AcircdegF Boiling Point 4377 AcircdegC 7911 AcircdegF Optical Properties Metric English Comments

Emissivity (0-1) 032 032 650 nm unoxidized total

Processing Properties

Annealing Temperature

gt= 705 AcircdegC gt= 1300 AcircdegF cold-rolled in vacuum

gt= 760 AcircdegC gt= 1400 AcircdegF hot-rolled gt= 1000 AcircdegC gt= 1830 AcircdegF solution

annealing for forged billets

Component

Elements Properties

Zirconium Zr 100 100 Descriptive Properties

Alpha Phase hcp lt 870AcircdegC

Crystal StructureBeta Phase Crystal Structure

bcc gt 870AcircdegC

CAS Number 7440-67-7

CHAPTER-3DESIGN

OVERVIEW

31 CMM DATA

311 GENERATION OF PRESSURE DISTRIBUTION DATA ON

THE BLADE

SURFACE

Last stage blade of steam turbine which is being analyzed for stress and vibration

is a highly twisted blade due to the variation if the blade speeds across the height of the

blade The deflection in the blade passage also reduces from hub to tip to vary the loading

on each section Thus the pressure distribution on the suction amp pressure surface of the

blade changes considerably from hub to tip to match the loading at that sectionIt is

known fact that the area of pressure distribution curve representing the blade loading

Hence it has been decided to generate the pressure distribution at all the lsquo17rsquo blade

sections

The following procedure allows to get the blade surface pressure distribution with the

help of BladeGen amp BladeGen plus package

From the blade coordinate input data file for suctionpressure surface x y z coordinate

of surface was generated as a loop with the following notations

X-along the height of the blade

Y- Meridional direction

Z-along blade to blade

2 Profile curve is generated with above coordinates of all sections placed one below

the other is sequence from section (1) to section (5 along the height of the blade The

coordinates between two section separated by lsquorsquo

3 Hub amp Shroud boundary is generated at the appropriate heights with ndashY negative

meridional axis corresponded from LE (Leading edge) And positive distance from

meridional distance from TE (Tailing Edge)

4 Hub Curve file is generated as follows

283450000 0000000000 -100000000

283450000 0000000000 0000000000

283450000 0000000000 1000000000

In between the values Comma is compulsory (X Y Z)

A profile contains total 60 points for all lsquo5rsquo sections

5 Profile Curve file is generated as follows

28345-574-2292

28345-523-2325

28345-446-2336

28345-343-2322

28345-215-2282

28345-066-2212

28345 103-2111

28345 285-1972

28345 474-1791

28345 661-1562

28345 832-1278

28345 966-939

28345 104-553

28345 1035-143

44265 1521-1551

44265 1564-1521

44265 1581-1469

44265 1574-1395

44265 1544-1299

44265 1491-1183

44265 1419-1049

44265 1326-899

44265 1214-736

44265 1079-566

44265 923-395

6 Shroud Curve File is generated as follows

44265 0 -100

44265 0 0

44265 0 100

32 LAYER OVER VIEW

A layer (or streamline) is defined as a meridional curve visible in the Meridional View

that represents surface of revolution Most layer types shown below represent curves

that are automatically created and updated as the Meridional Envelope (hub and shroud

curves leading and trailing edge curves) are modified

Fig31 Single Blade

Layers serve two key purposes

1) Layers are referenced by the working views (Angle Thickness and PrsSct Views) to

provide the meridional location of the views data sets

2) Layers specify where streamline data sets are to be constructed for export

MERIDIONAL PROFILES

The meridional profile is primarily determined by a set of curve (Hub Shroud

inlet and outlet) This data is modified with leading and trailing edge curves (and other

meridional control curves) to describe an interpolation surface or grid in axial (z) and

radial co-ordinates vs stream wise (u) and span wise (v) positions This interpolation grid

is used when defining the layer that the meridional profile stores which are reference by

the angle thickness and prssct curves and used to define location of op data sets

ANGLE AND THICKNESS SPANWISE DISTRIBUTIONS

BladeGen offers several options for controlling the span wise distribution of angle and

thickness values These options can be displayed by clicking the right mouse button in

the Angle or Thickness View and selecting Span wise Distribution Type sub-menu from

the resulting popup menu Note that it is allowable for the Angle View to have a

different Span wise Distribution type than the Thickness View The following Span wise

Distribution types are available

General

Ruled Element

Axial Element

General

The General Distribution is the default Span wise Distribution type The

parameter of interest (angle or thickness) is defined by curves on defining layers that use

various meridional coordinates from those layers Since these layers may have arbitrary

shapes that dont necessarily correspond to true streamlines BladeGen must first convert

their coordinates to true meridional coordinates (consistent with the meridional

interpolation grid) before using them to compute the parameters to generate a blade

Ruled Element

The Ruled Element Span wise Distribution type is only available in the Angle

ViewIn a ruled element blade the angular location is defined by a straight line drawn in

3D space between points at the span location on the hub and shroud The hub and shroud

curves are the master curves They control the generation of all other defining curves

Thus the hub and shroud curves are the only curves that the user can modify in the Span

wise Distribution type

When one of the defining curves is updated from the hub curve it obtains its location by

the intersection of the surface of revolution generated using the meridional streamline and

the lines drawn between corresponding pairs of points on the hub and shroud Once this

update occurs a conversion is made to trueMeridional coordinates using the same

method as in the general Span wise Distribution type

Axial Element

In an axial element blade the parameter of interest (angle or thickness) depends

exclusively on radial position (R) at each span location The hub curve is the master

curve it controls the curves for all of the other defining layers Thus the hub curve is the

only curve that the user can modify in this Span wise Distribution type When a defining

layer curve is updated from the hub curve it obtains its parameter (angle or thickness) at

a given meridional position by using an axial projection from the hub curve Once this

update occurs a conversion is made to true meridional coordinates using the same

When using axial element blades it is important to specify enough defining layers to

adequately describe the geometry of interest In most cases 5 layers are sufficientWhen

this distribution type is used in the Thickness View there is a menu command in the

popup menu to specify a taper angle The taper angle which normally defaults to zero is

limited to guarantee a minimum thickness of 10 of the specified value

Blade Settings

This section describes parameters and functions that apply to a single blade They are

accessed using either the Blade menu or the blade toolbar

BladeGen has the ability to design with splitter blades Splitter blades are blades

positioned between main blades for additional flow control Splitter blades can be

dependent on the main blade for their angular and thickness definitions or have their own

independent definitions

Like layers BladeGen has one active blade at a time Most views display only the data

pertaining to the active blade Only the Blade-to-Blade and 3D Views display all blades

AUXILIARY VIEW DETAILS

The Auxiliary View is used to display various data sets describing the model and is

automatically updated when modifications are performed in a Working View The values

displayed are calculated from the same data structures and functions that are used to

output geometry for other purposes

The following view types are available

Blade-to-Blade View

3D View

Meridional Contour View

Blade-To-Blade View

The Blade-to-Blade view shown below combines the meridional angular and

thickness descriptions of the blade along a streamline (called a layer) The blade is

displayed as a function of the distance along the streamline in the meridional view and its

angular position using one of three Coordinate Systems

Fig32 Blade-To-Blade ViewBlade-To-Blade View

3d View

This view allows the user to visualize the model in three dimensions as shown below

The model can be dynamically rotated panned and zoomed to achieve the desired

viewing perspective With material (surface) visibility and clipping plane controls the

user can choose to view a subset of the model in greater detail The user may also choose

to view multiple blades by using the replicates controls Like any other auxiliary view

the 3D view is automatically updated when a change is made in one of the working

Fig33 3d-View Of A Twisted Blade3d-View Of A Twisted Blade

Fig34 Total 3d-View Of An Axial Turbine RotorFront View Of An Axial Turbine Fig34 Total 3d-View Of An Axial Turbine RotorFront View Of An Axial Turbine

Fig35 Unstructured Mesh Model Of Rotor

BladeGen allows the user to plot contours of Theta Beta Lean or Thickness on

the meridional profile as shown below This view can be displayed using the View |

Auxiliary View Content | Meridional Contour View menu command or by pressing the

toolbar button (located by default on the right edge of the main window)

The Contour view can display the following values Theta (Blade Location) Beta (Blade

Angle) Blade Lean Angle Normal Thickness and Modified Thickness (Includes

OverUnder-Filing)

The user can select from several grid densities Very Fine Fine Medium and Course

These settings use predetermined point counts which are distributed using the lengths of

the four edges of the blade

Computer-aided design (CAD) also known as computer-aided design and drafting

(CADD) is the use of computer technology for the process of design and design-

documentation Computer Aided Drafting describes the process of drafting with a

computer CADD software or environments provide the user with input-tools for the

purpose of streamlining design processes drafting documentation and manufacturing

processes CADD output is often in the form of electronic files for print or machining

operations The development of CADD-based software is in direct correlation with the

processes it seeks to economize industry-based software (construction manufacturing

etc) typically uses vector-based (linear) environments whereas graphic-based software

utilizes raster-based (pixilated) environments

CADD environments often involve more than just shapes As in the manual drafting of

technical and engineering drawings the output of CAD must convey information such as

materials processes dimensions and tolerances according to application-specific

conventions

CAD may be used to design curves and figures in two-dimensional (2D) space or curves

surfaces and solids in three-dimensional (3D) objects

CAD is an important industrial art extensively used in many applications including

automotive shipbuilding and aerospace industries industrial and architectural design

prosthetics and many more CAD is also widely used to produce computer animation for

special effects in movies advertising and technical manuals The modern ubiquity and

power of computers means that even perfume bottles and shampoo dispensers are

designed using techniques unheard of by engineers of the 1960s Because of its enormous

economic importance CAD has been a major driving force for research in computational

geometry computer graphics (both hardware and software) and discrete differential

geometry

Current computer-aided design software packages range from 2D vector-based drafting

systems to 3D solid and surfacemodelers Modern CAD packages can also frequently

allow rotations in three dimensions allowing viewing of a designed object from any

desired angle even from the inside looking out Some CAD software is capable of

dynamic mathematic modeling in which case it may be marketed as CADD mdash

computer-aided design and drafting

CAD is used in the design of tools and machinery and in the drafting and design of all

types of buildings from small residential types (houses) to the largest commercial and

industrial structures (hospitals and factories)

CAD is mainly used for detailed engineering of 3D models andor 2D drawings of

physical components but it is also used throughout the engineering process from

conceptual design and layout of products through strength and dynamic analysis of

assemblies to definition of manufacturing methods of components It can also be used to

design objects

CAD has become an especially important technology within the scope of computer-aided

technologies with benefits such as lower product development costs and a greatly

shortened design cycle CAD enables designers to lay out and develop work on screen

print it out and save it for future editing saving time on their drawings

Types of CAD Software

2D CAD

Two-dimensional or 2D CAD is used to create flat drawings of products and structures

Objects created in 2D CAD are made up of lines circles ovals slots and curves 2D

CAD programs usually include a library of geometric images the ability to create Bezier

curves splines and polylines the ability to define hatching patterns and the ability to

provide a bill of materials generation Among the most popular 2D CAD programs are

AutoCAD CADkey CADDS 5 and Medusa

3D CAD

Three-dimensional (3D) CAD programs come in a wide variety of types intended for

different applications and levels of detail Overall 3D CAD programs create a realistic

model of what the design object will look like allowing designers to solve potential

problems earlier and with lower production costs Some 3D CAD programs include

Autodesk Inventor CoCreate Solid Designer ProEngineer SolidEdge SolidWorks

Unigraphics NX and VX CAD PROENGINEER V5

3D Wireframe and Surface Modeling

CAD programs that feature 3D wireframe and surface modeling create a skeleton-like

inner structure of the object being modeled A surface is added on later These types of

CAD models are difficult to translate into other software and are therefore rarely used

anymore

Solid Modeling

Solid modeling in general is useful because the program is often able to calculate the

dimensions of the object it is creating Many sub-types of this exist Constructive Solid

Geometry (CSG) CAD uses the same basic logic as 2D CAD that is it uses prepared

solid geometric objects to create an object However these types of CAD software often

cannot be adjusted once they are created Boundary Representation (Brep) solid modeling

takes CSG images and links them together Hybrid systems mix CSG and Brep to achieve

desired designs

34 INTRODUCTION TO PROENGINEER

ProENGINEER Wildfire is the standard in 3D product design featuring industry-leading

productivity tools that promote best practices in design while ensuring compliance with

your industry and company standards Integrated ProENGINEER CADCAMCAE

solutions allow you to design faster than ever while maximizing innovation and quality

to ultimately create exceptional products

Customer requirements may change and time pressures may continue to mount but your

product design needs remain the same - regardless of your projects scope you need the

powerful easy-to-use affordable solution that ProENGINEER provides

ProENGINEER Wildfire Benefits

bullUnsurpassed geometry creation capabilities allow superior product differentiation and

manufacturability

bullFully integrated applications allow you to develop everything from concept to

manufacturing within one application

bullAutomatic propagation of design changes to all downstream deliverables allows you to

design with confidence

bullComplete virtual simulation capabilities enable you to improve product performance and

exceed product quality goals

bullAutomated generation of associative tooling design assembly instructions and machine

code allow for maximum production efficiency

Pro ENGINEER can be packaged in different versions to suit your needs from

ProENGINEER Foundation XE to Advanced XE Package and Enterprise XE Package

ProENGINEER Foundation XE Package brings together a broad base of functionality

From robust part modeling to advanced surfacing powerful assembly modeling and

simulation your needs will be met with this scalable solution Flex3C and Flex

Advantage Build on this base offering extended functionality of your choosing

DIFFERENT MODULES IN PROENGINEER

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

Design will be created by considering the main consideration ie failures of the turbine

blade The break down and failures of turbo machineries have been influencing such as

consequential damages hazards to public life and most importantly the cost to repairs To

avoid these it is obvious that the balding of turbo machinery must be made structurally

stronger that means not in dimensions andor use of materials of construction but

keeping the operating stresses well within the limits

Turbo machinery blades are classified into two categories depending on their

manner of operation as either impulse or reaction blades Impulse blades function by

redirecting the passing fluid (steam or gas) flow through a specified angle A work

producing force is developed by resulting change of momentum of passing fluid flow

Reaction blades function as airfoils by developing a gas dynamic lift from the

pressure difference which the airfoil causes between the blades upper and lower

surfaces High-pressure stages are generally impulse stages and low-pressure stages are

reaction stages Thus a single free standing blade can be considered as pre-twisted

continuous beam with an asymmetric airfoil cross-section mounted at a stagger angle on

a rotating disc

Failure of bladed disc

Excessive stresses

Resonance due to vibration

Operating environmental effects

Ever increasing demands of high performance together with reliability of

operation long life and lightweight necessitate consistent development of almost every

part of steam turbine blades from a vital part of a turbo machine Apart from their shape

and geometry on which the performance characteristics of the machine largely depend

their dynamic strength is of considerable importance as far as the reliability operation and

life of the engine are concerned High cycle fatigue plays a significant role in many

turbine blade failures During operation periodic fluctuations in the steam force occur at

frequencies

Corresponding to the operating speed and harmonics and cause the bladed disk to vibrate

The amplitude of these vibrations depends in part of the natural frequencies of the bladed

disk to the forcing frequency Large amplitude vibration can occur when the forcing

frequency approaches or becomes resonant with the natural frequency of the blades

Dynamic stresses associated with near resonant or resonant vibration produce high cycle

fatigue damage and can initiate and propagate cracks very quickly Steam turbine

manufacturers typically design and manufacture blades with adequate margins between

the forcing frequencies and the fundamental natural frequencies to avoid resonance

REASONS FOR FAILURES IN STEAM TURBINE BLADES

In the following paragraphs various failure modes of the turbine blade are discussed

along with different kinds of stresses in the blade and the nature of aerodynamic

excitation A brief discussion of each of the above failure mechanisms follows in order

to understand their significance

Excessive stress

The total stress at any location of the blade is sum of the centrifugal tension

centrifugal bending steady steam bending and the alternating bending The amplitude of

alternating bending depends on the dynamic bending force damping factor and the

resonant frequency Each of these is briefly discussed below to highlight their

importance

Centrifugal stress

In steam turbine centrifugal stress is never the main cause of a blade failure

except in the rare cases of turbine run-away or due to low cycle fatigue caused by

frequent start upsshut downs However centrifugal stress is an important contributing

factor with fatigue failure corrosion fatigue failure and stress corrosion failures The

level of centrifugal stress is kept at such a level so as to have enough margins for

alternating stress The blade configuration is designed so as to keep the center of gravity

of shroud airfoil and root attachments on a common radial axis This prevents

centrifugal induced torsion stresses Using any of the standard FEM packages can best

carry out analysis of centrifugal stress

Steam induced stress ndash steady state

Steam being the driving force exerts loads on the blade due to steam pressure

from the pressure side of the blade profile thereby inducing bending stresses This

bending stress is superimposed on the centrifugal tension Although the net value of

steady bending load and centrifugal stress alone is not normally a cause of blade failure

this is the basis for the majority of failures arising due to vibratory stresses superimposed

upon them

Steam induced stress ndash Alternating

Steam induced alternating stress can be induced by interrupted arc of admission

nozzle wake at nozzle passing frequency mismatch of diaphragm nozzle at horizontal

split andor missing diaphragm blades nozzle pitch variation poor nozzle profile etc

Estimation of the vibratory stress caused by these requires the analysis of the response

of the blade to the excitation forces caused by these Obviously the inputs to such an

analysis are the excitation levels the damping natural frequency and the mode shape of

the blade vibration Disk vibrations which can get excited due to variety of reasons can

also cause high stresses in the blade roots leading to failure This aspect of blade

stressing is quite involved and many a time difficult to compute correctly

Impact stress

Impact stress arises due to entrapment of a foreign body such as broken valve

spindles strainers etc This may result in a chain reaction and can cause failure in many

downstream rotating and stationary blades Impact stress also results due to water ingress

and at times due to steam hammer and from rubbing of blades in the event of failure of

the thrust bearing

Low cycle fatigue

Low cycle fatigue is caused by frequent startstop operations thermal cycling and

frequent water slugging or water washing due to inadequate water drainage in the casing

and can cause failures within few hundreds to a few thousands stress cycle

Thermal fatigue

Thermal fatigues is a low cycle fatigue process as a result of thermal stress caused

due to quick starting rapid and frequent load changing steam temperature cycling and

water slugging Considerable thermal stresses are generated due to the temperature

differential since blade foil is in direct contact with the nozzle upstream temperature

whereas much cooler spent steam cools shroud root and disk

Creep stress

Creep stress failures are rare but cracking at locations with high stress

concentrations may take place if design is inadequate Hence high temperature stages

should have larger fillet radii at the root

Resonant vibration

Vibration is important in designing turbine bladesdisk since resonant vibratory

stresses sustained over a period of time can cause fatigue failures The period of time

need not be large since a 500Hz vibration accumulates 2 million cycles in an hour and

108 cycles in 2 days Bladed disk poses a worst vibratory fatigue problem since it is

directly exposed to a wide range of aerodynamic excitation and failure can result when

any of the following matching takes place

A rotating turbine blade (bucket) is the components which converts the energy of

flowing fluid into mechanical energy Thus the reliability of these blades is very

important for successful operation of turbine Metallurgical examinations of failed blades

show that almost all the failures can be attributed to the fatigue of metal Fluctuating

forces in combination with the steady forces cause fatigue failure

Turbo machine experience fluctuating forces when they pass through non-uniform

fluid from stationary vanes (nozzle) The basic design consideration is to avoid or to

minimize the dynamic stresses due to fluctuating force Based on the vibration of the

mechanical structures the dynamic behavior of turbine blade blades or the bladed disc

assembly can be predicted

The present work presents an approach for modeling of blades bladed disc amp for

its vibration analysis Generally turbo machine low-pressure stage blades are long

twisted amp tapered so it needs lot of input data to accurately define the complete

geometry Blade geometry is defined by giving different profile data at

Different heights To reduce the pains for creation of solid model of this type of blades a

program file called as macro was developed in ansys command From these macros solid

model was created

Finite element method for the single blade solid model was created with eight

nodded quadrilateral brick element in ansys

Two types of analysis was done for this present work

Free standing blade static analysis

Free standing blade model analysis

The maximum number of nodal diameters in bladed disc assembly is half the

number of blades (for an even number of blades) For the disc having an odd number of

the blades the maximum nodal diameter is (number of blades-1)2

For free standing blade root supports stiffness effect was studied and frequency at

different rotating speeds also calculated Analytical work to determine the blade

characteristics calls for accurately modeling the geometry

Results obtained through analytical work makes quite closely with experimental

work confirming the accuracy of the model and the adequacy of assumed boundary

conditions

A turbo machine blade is usually a cantilever beam or plate is tapered and twisted with

an airfoil cross-section Typically a turbo machine has several stages each stage with a

stator and rotor In the stator they are all inserted as diaphragms or nozzles in a ring to

guide the flow medium at an appropriate entry angle into rotor blades The rotor blades

are mounted on a disc at a stagger angle to the machine axis and they convert the thermal

energy into mechanical energy in turbine In turbine steam enters at high pressure and

temperature in the first stage and expands while passing through the several stages before

it is let out from the last

Stage with low temperature and pressure after extracting as much as thermal energy as

possible Hence the short blades in high pressure have high frequency of the order of

1000Hz which becomes progressively lower about 100Hz in the last stage long blades

In the compressor stage the operation principle is reversed to compress the gases

utilizing the supplied mechanical power

A typical rotor blades sees upstream disturbances from the stator row and as it rotates

receives a corresponding number of increasing and decreasing lift and moment

alternating periodically depending on the number of stator bladesnozzlesguide vanes A

stator blade can also be imagined to rotate in an opposite direction to the rotor relative to

the moving row and thus receives a corresponding number of periodic forces and

moments equal to the rotor blades An ideal placement of blades in the stator is not

feasible in practice Firstly the blades are not all identical in their cross section along the

length their pitch distance from blade to blade varies and the axial and angular locations

will have some errors in mounting them in the stator housing Because of these errors in

the stator mechanical excitation at rotational speed and its harmonics occurs on the rotor

blades

Natural frequency and mode shape

Natural frequency is the frequency at which an object vibrates when excited by a force

such as a sharp blow from a hammer At this frequency the structure offers the least

resistance to a force and if left uncontrolled failure can occur Mode shape is the way in

which the object deflects at this frequency An example of natural frequency and mode

shape is given in the case of a guitar string When struck the string vibrates at a certain

frequency and attains deflection shape

The frequency can be noted by the pitch coming from the string Different string

geometries lead to different natural frequencies or notes By nature of its structure a

turbine blade has many natural frequencies and mode shapes These frequencies and

mode shapes are somewhat further complicated by the use of shroud to connect group of

blades together

MODEL PREPARATION AND FORMATION

Solid modeling is the first step for doing any analysis and testing and it gives physical

picture for new products FEM models can easily create from solid models by the

process of meshing FEM models can be made manually but it is for simple cases only

If the model is of complex shape only way for preparing FEM model is ldquomeshing the

solid modelrdquo

While dealing with complex blade structures such as blades with root or blades

with coupling from disc or shroud development of special purpose finite element

packages becomes too involved In those cases it becomes handy to adopt some well-

established finite element codes and couple them with information from aerodynamics

and damping models Some of the important commercial codes available are

NASTRAN ANSYS NISA SDRC I-DEAS etc here we will consider the application of

ANSYS software to model a Low Pressure last stage turbine blade with its root

Fig36 Assembly of CMM data by a curve

Fig37 CMM data free curves (3D CURVES)

Fig38 solid blade view

Fig39 final model in 3D

CHAPTER-4ANALYSIS

OFSTEAM TURBINE BLADE

INTRODUCTION TO FEA

Finite Element Analysis (FEA) was first developed in 1943 by R Courant who utilized

the Ritz method of numerical analysis and minimization of variational calculus to obtain

approximate solutions to vibration systems Shortly thereafter a paper published in 1956

by M J Turner R W Clough H C Martin and L J Topp established a broader

definition of numerical analysis The paper centered on the stiffness and deflection of

complex structures

By the early 70s FEA was limited to expensive mainframe computers generally owned

by the aeronautics automotive defense and nuclear industries Since the rapid decline in

the cost of computers and the phenomenal increase in computing power FEA has been

developed to an incredible precision Present day supercomputers are now able to

produce accurate results for all kinds of parameters

FEA consists of a computer model of a material or design that is stressed and analyzed

for specific results It is used in new product design and existing product refinement A

company is able to verify a proposed design will be able to perform to the clients

specifications prior to manufacturing or construction Modifying an existing product or

structure is utilized to qualify the product or structure for a new service conditionIn case

of structural failure FEA may be used to help determine the design modifications to meet

the new condition

There are generally two types of analysis that are used in industry 2-D modeling and 3-

D modeling While 2-D modeling conserves simplicity and allows the analysis to be run

on a relatively normal computer it tends to yield less accurate results 3-D modeling

however produces more accurate results while sacrificing the ability to run on all but the

fastest computers effectively Within each of these modeling schemes the programmer

can insert numerous algorithms (functions) which may make the system behave linearly

or non-linearly Linear systems are far less complex and generally do not take into

account plastic deformation Non-linear systems do account for plastic deformation and

many also are capable of testing a material all the way to fracture

FEA uses a complex system of points called nodes which make a grid called a mesh This

mesh is programmed to contain the material and structural properties which define how

the structure will react to certain loading conditions Nodes are assigned at a certain

density throughout the material depending on the anticipated stress levels of a particular

area Regions which will receive large amounts of stress usually have a higher node

density than those which experience little or no stress Points of interest may consist of

fracture point of previously tested material fillets corners complex detail and high

stress areas The mesh acts like a spider web in that from each node there extends a mesh

element to each of the adjacent nodes This web of vectors is what carries the material

properties to the object creating many elements

A wide range of objective functions (variables within the system) are available for

minimization or maximization

Mass volume temperature

Strain energy stress strain

Force displacement velocity acceleration

Synthetic (User defined)

There are multiple loading conditions which may be applied to a system Some examples

are shown

Point pressure thermal gravity and centrifugal static loads

Thermal loads from solution of heat transfer analysis

Enforced displacements

Heat flux and convection

Point pressure and gravity dynamic loads

Each FEA program may come with an element library or one is constructed over time

Some sample elements are

Rod elements

Beam elements

PlateShellComposite elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

Viscous damping elements

Many FEA programs also are equipped with the capability to use multiple materials

within the structure such as

Isotropic identical throughout

Orthotropic identical at 90 degrees

General anisotropic different throughout

Types of Engineering Analysis

Structuralanalysis consists of linear and non-linear models Linear models use simple

parameters and assume that the material is not plastically deformed Non-linear models

consist of stressing the material past its elastic capabilities The stresses in the material

then vary with the amount of deformation as in

Vibrationalanalysis is used to test a material against random vibrations shock and

impact Each of these incidences may act on the natural vibrational frequency of the

material which in turn may cause resonance and subsequent failure

Fatigueanalysis helps designers to predict the life of a material or structure by showing

the effects of cyclic loading on the specimen Such analysis can show the areas where

crack propagation is most likely to occur Failure due to fatigue may also show the

damage tolerance of the material

Heat Transfer analysis models the conductivity or thermal fluid dynamics of the

material or structure This may consist of a steady-state or transient transfer Steady-state

transfer refers to constant thermo properties in the material that yield linear heat

diffusion

41 INTRODUCTION TO ANSYS

small pieces (of user-designated size) called elements The software implements

equations that govern the behaviour of these elements and solves them all creating a

comprehensive explanation of how the system acts as a whole These results then can be

presented in tabulated or graphical forms This type of analysis is typically used for the

design and optimization of a system far too complex to analyze by hand Systems that

may fit into this category are too complex due to their geometry scale or governing

equations

ANSYS is the standard FEA teaching tool within the Mechanical Engineering

Department at many colleges ANSYS is also used in Civil and Electrical Engineering as

well as the Physics and Chemistry departments

ANSYS provides a cost-effective way to explore the performance of products or

processes in a virtual environment This type of product development is termed virtual

prototyping

With virtual prototyping techniques users can iterate various scenarios to optimize the

product long before the manufacturing is started This enables a reduction in the level of

risk and in the cost of ineffective designs The multifaceted nature of ANSYS also

provides a means to ensure that users are able to see the effect of a design on the whole

behavior of the product be it electromagnetic thermal mechanical etc

Static analysis Chrome steel

Fig41 The above image is imported from Pro-e to Ansys using IGES (Initial Graphical Exchange Specification) format

Fig42 The above image is showing meshing is used to divide the problem into

number of small problems and also to apply the material and element properties

Fig43 The above image showing loads acting on spring

Fig44 The above image is showing distributed shape or variation of

geometry shape after applying loads The maximum displacement is 0147608 mm

Fig45 The above image is showing vonmises stress value Vonmises stress

depends on vonmises theory of failure

Fig46 The above image is first mode shape of turbine blade having 11174

and also the first mode is considered as natural frequency of object

Fig47 The above image is the second mode shape having frequency 2356

Fig48 The above image is the third mode shape having frequency 66537

Fig49 The above image is the fourth mode shape having frequency 68111

Fig410 The above image is the fifth mode shape having frequency 12003

Static analysisTitanium

Fig411The above image is showing distributed shape or variation of

Fig412 The above image is showing von-misses stress value Von-misses stress

depends on von-misses theory of failure

Fig413 The above image is first mode shape of turbine blade having

11154 and also the first mode is considered as natural frequency of object

Fig417 The above image is the fifth mode shape having 118454

Thermal Analysis Chrome steel

Fig418 The above image is showing thermal loads

Fig419 The above image showing the Temperature Distribution

Fig420 The above image is showing the Thermal Gradient sum

Fig421The above image is showing the Thermal Flux sum

Thermal Analysis Titanium

Fig425 The above image is showing the Thermal Flux sum

Ceramic coating Static analysis

Fig426 The above image is imported from Pro-E to Ansys using IGES

(Initial Graphical Exchange Specification) format

Fig429 The above image is first mode shape of turbine blade having 10522 and

also the first mode is considered as natural frequency of object

Fig433 The above image is the fifth mode shape having mode shape 116057

Thermal analysis of ceramic coating

Fig434 The above image is showing the thermal loads

Fig436 The above image is showing the thermal flux

Fig437 The above image is showing the thermal gradient sum

CHAPTER-5RESULTS OF THE

ANALYSISON

BLADES

RESULTS TABLE

The results table is explained in the below graphs by comparing with each other

The values shown in the above table are taken from the thermal and structural analysis of

the blade using ansys software

The materials are shown in the graphs are listed as like mentioned below

1 Chrome Steel

2 Titanium

3 Cast Iron coated with Zirconium

chrome steel Titanium Cast Iron With Zirconium coating

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

Temperature(degc) 533 533 533

Thermal gradient(degcmm)

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Stress(N〖 mm〗 ^2)

The maximum stress applied on the blade is represented on the graph which will give a brief explanation that relatively it is low on the applied new material

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

The above chart explains that the displacement due to the stresses is less compared to generally used materials for the applied new material

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

Comparatively the temperature on the surface of the blade is same for all materials So this shows that there is nothing changed and no loss by introducing new material

1 2 30

8007150549999999

605119

Relatively thermal gradient is less for the new applied material So it is an advantage for intro of zirconium coated cast iron

Thermal flux(Wmm2)

1 2 30

1172710287

Thermal flux(W〖 mm〗 ^2)

Relatively the thermal flux is high compared to other general materials So it is an advantage

CHAPTER-6CONCLUSION

CONCLUSION

In this project we have analyzed previous designs and generals of turbine blade to do

further optimization Finite element results for free standing blades give a complete

picture of structural characteristics which can utilized for the improvement in the design

and optimization of the operating conditions

In the first step we have designed turbine blade using CMM data from existing model

In the second step we have done the study on different materials which are suitable for

the improvement of turbine blade

In the third step we have validated our design using existing materials

In the next step we have applied different materials for turbine blade to suggest best

material

From the above results we can conclude that using cast iron with partially stabilized

zirconium coating is more beneficial than previous materials due to low stress

displacement good thermal strength low cost and easy to manufacture

CHAPTER-7BIBLIOGRAPHY

References

1 RaoJS application of variational principle to shrouded turbine blades

Proceedings of 19th cong ISTAM 1974 pp 93-97

2 LeissaAW MacbainJC and KeilbRE Vibration of twisted cantilever plates

summary of provisions current studies Journal of Sound and Vibration 1984

Vol-96 (20) pp 159-167

3 Tsuneo Tsuiji Teisuke Sueoka Vibrational analysis of twisted thin cylindrical

panels by using Raleigh-Ritz method JSME International Journal Series iii

1990 volume 33 pp 501-505

4 Le-Chung Shiau Teng-Yuan Wu Free vibration of buckled laminated plates

by finite element method Transactions of the ASME Journal of Vibrations

and Accoustics October 1997 volume 111 pp 635-644

5 Hu XX and TTsuiji free vibrational analysis of curved and twisted cylindrical

thin panels Journal of sound and vibration Jan7 1999vol-219 (1) pp 63-68

6 YooHH JYkwak and JChung Vibrational analysis of rotating pre twisted

blades with a concentrated mass Journal of sound and vibration Mar 2001

Vol 240(5) pp 891-908

7 Park Jung-Yong Jung Yong-Keun Park Jong-Jin Kang Yong-Ho

Dynamic analysis method for prevention of failure in the 1st stage low

pressure turbine blade with 2 fingers root Proceedings of SPIE - The

International Society for Optical Engineering 2001 vol 4537 pp 209-212

8 AHShah GSRamsekhar and YMDesai Natural vibrations of laminated

composite beams by using fixed finite element modeling Journal of sound

and vibration 2002 Vol 257 pp 635-651

9 JSRao RBahree AMSharan The design of rotor blades taking into

account the combined effects of vibratory and thermal loads transactions of

the ASME Journal of Engineering gas Turbines and Power oct-1989 vol-

111 pp 610-618

10 Wjkeartonsteam turbine theory and practice1992 7th edition pp423-450

2D CAD

3D CAD

Solid Modeling

ONGOLE ndash 523 272 AP

VENGAMUKKA PALEM ndash 523272 AP

DEPARTMENT OF MECHANICAL ENGINEERINGCERTIFICATE

This is to certify that the project entitled

ldquoOPTIMIZATION OF STEAM TURBINE BLADE MATERIAL amp ITS

ANALYSISrdquois a bonafied work of the following final BTech studentsin

the partial fulfillment of the requirement for the award of the degree of

Bachelor of Technology inMECHANICAL ENGINEERING

for the academic year 2009-13

VSURENDRA KUMAR

GCALEB PAUL ARAHUL

MLOKESH GSIVA

Signature of guide Signature of Head of DepartmentMrKCHANDRASEKHAR Dr BSRMURTHY MTech( PhD) MTechPhD

DECLARATION

ARAHULMLOKESH

ACKNOWLEDGEMENT

ARAHULMLOKESH

ABSTRACT

zirconium coating

CONTENTS-

11 INTRODUCTION

CONCEPT

31CMM DATA

32 LAYER OVERVIEW

35DESIGN OF BLADE

11 INTRODUCTION

STEAM TURBINE-

BLADE-

material used

blades

machine as follows

2 LENGTH CUTTING

3 THICKNESS MILLING

6 RHOMBOID GRINDING

be within 8 microns

Program

12 CONCAVE MILLING

13 TAPER MILLING

DESIGN

PROPERTIES

Cast Iron

Physical Properties

0200 - 0282

lbinAcircsup3

Hardness Brinell

Hardness Knoop

Hardness Rockwell B

Hardness Rockwell C

Hardness Vickers

118 - 1650 MPa

17100 - 240000 psi

655 - 1450 MPa

9500 - 210000 psi

Elongation at Break

100 - 250 100 - 250

Reduction of Area

200 - 100 200 - 100

621 - 240 GPa 9000 - 34800 ksi

248 - 655 MPa 36000 - 95000 psi

331 - 2520 MPa

48000 - 365000 psi

Poissons Ratio

0240 - 0370 0240 - 0370

Fatigue Strength

689 - 510 MPa

10000 - 74000 psi

Fracture Toughness

Machinability

0000 - 125 0000 - 125

Shear Modulus

270 - 676 GPa

3920 - 9800 ksi

Shear Strength

149 - 1480 MPa

21600 - 215000 psi

400 - 244 J 295 - 180 ft-lb

407 - 123 J 300 - 910 ft-lb

000000500 - 110 ohm-cm

000000500 - 110

ohm-cm

Thermal

AcircdegF

113 - 533 Wm-K

784 - 370 BTU-inhr-

Melting Point

Shrinkage 0800 - 150 0800 - 150

Zirconium Zr

Characteristics

Applications

Physical

Chemical Properties

Equivalent

945 GPa 13700 ksi

00000400 ohm-cm 00000400 ohm-cm

000000134 000000134 cgsg

Thermal Properties

Component

Elements Properties

bcc gt 870AcircdegC

CHAPTER-3DESIGN

OVERVIEW

31 CMM DATA

THE BLADE

SURFACE

sections

283450000 0000000000 -100000000

283450000 0000000000 0000000000

283450000 0000000000 1000000000

28345-574-2292

28345-523-2325

28345-446-2336

28345-343-2322

28345-215-2282

28345-066-2212

28345 103-2111

28345 285-1972

28345 474-1791

28345 661-1562

28345 832-1278

28345 966-939

28345 104-553

28345 1035-143

44265 1521-1551

44265 1564-1521

44265 1581-1469

44265 1574-1395

44265 1544-1299

44265 1491-1183

44265 1419-1049

44265 1326-899

44265 1214-736

44265 1079-566

44265 923-395

44265 0 -100

44265 0 0

44265 0 100

32 LAYER OVER VIEW

Fig31 Single Blade

MERIDIONAL PROFILES

General

Ruled Element

Axial Element

General

Ruled Element

Axial Element

Blade Settings

Blade-to-Blade View

3D View

Blade-To-Blade View

3d View

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

DECLARATION

ARAHULMLOKESH

ACKNOWLEDGEMENT

ARAHULMLOKESH

ABSTRACT

zirconium coating

CONTENTS-

11 INTRODUCTION

CONCEPT

31CMM DATA

32 LAYER OVERVIEW

35DESIGN OF BLADE

11 INTRODUCTION

STEAM TURBINE-

BLADE-

material used

blades

machine as follows

2 LENGTH CUTTING

3 THICKNESS MILLING

6 RHOMBOID GRINDING

be within 8 microns

Program

12 CONCAVE MILLING

13 TAPER MILLING

DESIGN

PROPERTIES

Cast Iron

Physical Properties

0200 - 0282

lbinAcircsup3

Hardness Brinell

Hardness Knoop

Hardness Rockwell B

Hardness Rockwell C

Hardness Vickers

118 - 1650 MPa

17100 - 240000 psi

655 - 1450 MPa

9500 - 210000 psi

Elongation at Break

100 - 250 100 - 250

Reduction of Area

200 - 100 200 - 100

621 - 240 GPa 9000 - 34800 ksi

248 - 655 MPa 36000 - 95000 psi

331 - 2520 MPa

48000 - 365000 psi

Poissons Ratio

0240 - 0370 0240 - 0370

Fatigue Strength

689 - 510 MPa

10000 - 74000 psi

Fracture Toughness

Machinability

0000 - 125 0000 - 125

Shear Modulus

270 - 676 GPa

3920 - 9800 ksi

Shear Strength

149 - 1480 MPa

21600 - 215000 psi

400 - 244 J 295 - 180 ft-lb

407 - 123 J 300 - 910 ft-lb

000000500 - 110 ohm-cm

000000500 - 110

ohm-cm

Thermal

AcircdegF

113 - 533 Wm-K

784 - 370 BTU-inhr-

Melting Point

Shrinkage 0800 - 150 0800 - 150

Zirconium Zr

Characteristics

Applications

Physical

Chemical Properties

Equivalent

945 GPa 13700 ksi

00000400 ohm-cm 00000400 ohm-cm

000000134 000000134 cgsg

Thermal Properties

Component

Elements Properties

bcc gt 870AcircdegC

CHAPTER-3DESIGN

OVERVIEW

31 CMM DATA

THE BLADE

SURFACE

sections

283450000 0000000000 -100000000

283450000 0000000000 0000000000

283450000 0000000000 1000000000

28345-574-2292

28345-523-2325

28345-446-2336

28345-343-2322

28345-215-2282

28345-066-2212

28345 103-2111

28345 285-1972

28345 474-1791

28345 661-1562

28345 832-1278

28345 966-939

28345 104-553

28345 1035-143

44265 1521-1551

44265 1564-1521

44265 1581-1469

44265 1574-1395

44265 1544-1299

44265 1491-1183

44265 1419-1049

44265 1326-899

44265 1214-736

44265 1079-566

44265 923-395

44265 0 -100

44265 0 0

44265 0 100

32 LAYER OVER VIEW

Fig31 Single Blade

MERIDIONAL PROFILES

General

Ruled Element

Axial Element

General

Ruled Element

Axial Element

Blade Settings

Blade-to-Blade View

3D View

Blade-To-Blade View

3d View

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

ACKNOWLEDGEMENT

ARAHULMLOKESH

ABSTRACT

zirconium coating

CONTENTS-

11 INTRODUCTION

CONCEPT

31CMM DATA

32 LAYER OVERVIEW

35DESIGN OF BLADE

11 INTRODUCTION

STEAM TURBINE-

BLADE-

material used

blades

machine as follows

2 LENGTH CUTTING

3 THICKNESS MILLING

6 RHOMBOID GRINDING

be within 8 microns

Program

12 CONCAVE MILLING

13 TAPER MILLING

DESIGN

PROPERTIES

Cast Iron

Physical Properties

0200 - 0282

lbinAcircsup3

Hardness Brinell

Hardness Knoop

Hardness Rockwell B

Hardness Rockwell C

Hardness Vickers

118 - 1650 MPa

17100 - 240000 psi

655 - 1450 MPa

9500 - 210000 psi

Elongation at Break

100 - 250 100 - 250

Reduction of Area

200 - 100 200 - 100

621 - 240 GPa 9000 - 34800 ksi

248 - 655 MPa 36000 - 95000 psi

331 - 2520 MPa

48000 - 365000 psi

Poissons Ratio

0240 - 0370 0240 - 0370

Fatigue Strength

689 - 510 MPa

10000 - 74000 psi

Fracture Toughness

Machinability

0000 - 125 0000 - 125

Shear Modulus

270 - 676 GPa

3920 - 9800 ksi

Shear Strength

149 - 1480 MPa

21600 - 215000 psi

400 - 244 J 295 - 180 ft-lb

407 - 123 J 300 - 910 ft-lb

000000500 - 110 ohm-cm

000000500 - 110

ohm-cm

Thermal

AcircdegF

113 - 533 Wm-K

784 - 370 BTU-inhr-

Melting Point

Shrinkage 0800 - 150 0800 - 150

Zirconium Zr

Characteristics

Applications

Physical

Chemical Properties

Equivalent

945 GPa 13700 ksi

00000400 ohm-cm 00000400 ohm-cm

000000134 000000134 cgsg

Thermal Properties

Component

Elements Properties

bcc gt 870AcircdegC

CHAPTER-3DESIGN

OVERVIEW

31 CMM DATA

THE BLADE

SURFACE

sections

283450000 0000000000 -100000000

283450000 0000000000 0000000000

283450000 0000000000 1000000000

28345-574-2292

28345-523-2325

28345-446-2336

28345-343-2322

28345-215-2282

28345-066-2212

28345 103-2111

28345 285-1972

28345 474-1791

28345 661-1562

28345 832-1278

28345 966-939

28345 104-553

28345 1035-143

44265 1521-1551

44265 1564-1521

44265 1581-1469

44265 1574-1395

44265 1544-1299

44265 1491-1183

44265 1419-1049

44265 1326-899

44265 1214-736

44265 1079-566

44265 923-395

44265 0 -100

44265 0 0

44265 0 100

32 LAYER OVER VIEW

Fig31 Single Blade

MERIDIONAL PROFILES

General

Ruled Element

Axial Element

General

Ruled Element

Axial Element

Blade Settings

Blade-to-Blade View

3D View

Blade-To-Blade View

3d View

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

ABSTRACT

zirconium coating

CONTENTS-

11 INTRODUCTION

CONCEPT

31CMM DATA

32 LAYER OVERVIEW

35DESIGN OF BLADE

11 INTRODUCTION

STEAM TURBINE-

BLADE-

material used

blades

machine as follows

2 LENGTH CUTTING

3 THICKNESS MILLING

6 RHOMBOID GRINDING

be within 8 microns

Program

12 CONCAVE MILLING

13 TAPER MILLING

DESIGN

PROPERTIES

Cast Iron

Physical Properties

0200 - 0282

lbinAcircsup3

Hardness Brinell

Hardness Knoop

Hardness Rockwell B

Hardness Rockwell C

Hardness Vickers

118 - 1650 MPa

17100 - 240000 psi

655 - 1450 MPa

9500 - 210000 psi

Elongation at Break

100 - 250 100 - 250

Reduction of Area

200 - 100 200 - 100

621 - 240 GPa 9000 - 34800 ksi

248 - 655 MPa 36000 - 95000 psi

331 - 2520 MPa

48000 - 365000 psi

Poissons Ratio

0240 - 0370 0240 - 0370

Fatigue Strength

689 - 510 MPa

10000 - 74000 psi

Fracture Toughness

Machinability

0000 - 125 0000 - 125

Shear Modulus

270 - 676 GPa

3920 - 9800 ksi

Shear Strength

149 - 1480 MPa

21600 - 215000 psi

400 - 244 J 295 - 180 ft-lb

407 - 123 J 300 - 910 ft-lb

000000500 - 110 ohm-cm

000000500 - 110

ohm-cm

Thermal

AcircdegF

113 - 533 Wm-K

784 - 370 BTU-inhr-

Melting Point

Shrinkage 0800 - 150 0800 - 150

Zirconium Zr

Characteristics

Applications

Physical

Chemical Properties

Equivalent

945 GPa 13700 ksi

00000400 ohm-cm 00000400 ohm-cm

000000134 000000134 cgsg

Thermal Properties

Component

Elements Properties

bcc gt 870AcircdegC

CHAPTER-3DESIGN

OVERVIEW

31 CMM DATA

THE BLADE

SURFACE

sections

283450000 0000000000 -100000000

283450000 0000000000 0000000000

283450000 0000000000 1000000000

28345-574-2292

28345-523-2325

28345-446-2336

28345-343-2322

28345-215-2282

28345-066-2212

28345 103-2111

28345 285-1972

28345 474-1791

28345 661-1562

28345 832-1278

28345 966-939

28345 104-553

28345 1035-143

44265 1521-1551

44265 1564-1521

44265 1581-1469

44265 1574-1395

44265 1544-1299

44265 1491-1183

44265 1419-1049

44265 1326-899

44265 1214-736

44265 1079-566

44265 923-395

44265 0 -100

44265 0 0

44265 0 100

32 LAYER OVER VIEW

Fig31 Single Blade

MERIDIONAL PROFILES

General

Ruled Element

Axial Element

General

Ruled Element

Axial Element

Blade Settings

Blade-to-Blade View

3D View

Blade-To-Blade View

3d View

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

CONTENTS-

11 INTRODUCTION

CONCEPT

31CMM DATA

32 LAYER OVERVIEW

35DESIGN OF BLADE

11 INTRODUCTION

STEAM TURBINE-

BLADE-

material used

blades

machine as follows

2 LENGTH CUTTING

3 THICKNESS MILLING

6 RHOMBOID GRINDING

be within 8 microns

Program

12 CONCAVE MILLING

13 TAPER MILLING

DESIGN

PROPERTIES

Cast Iron

Physical Properties

0200 - 0282

lbinAcircsup3

Hardness Brinell

Hardness Knoop

Hardness Rockwell B

Hardness Rockwell C

Hardness Vickers

118 - 1650 MPa

17100 - 240000 psi

655 - 1450 MPa

9500 - 210000 psi

Elongation at Break

100 - 250 100 - 250

Reduction of Area

200 - 100 200 - 100

621 - 240 GPa 9000 - 34800 ksi

248 - 655 MPa 36000 - 95000 psi

331 - 2520 MPa

48000 - 365000 psi

Poissons Ratio

0240 - 0370 0240 - 0370

Fatigue Strength

689 - 510 MPa

10000 - 74000 psi

Fracture Toughness

Machinability

0000 - 125 0000 - 125

Shear Modulus

270 - 676 GPa

3920 - 9800 ksi

Shear Strength

149 - 1480 MPa

21600 - 215000 psi

400 - 244 J 295 - 180 ft-lb

407 - 123 J 300 - 910 ft-lb

000000500 - 110 ohm-cm

000000500 - 110

ohm-cm

Thermal

AcircdegF

113 - 533 Wm-K

784 - 370 BTU-inhr-

Melting Point

Shrinkage 0800 - 150 0800 - 150

Zirconium Zr

Characteristics

Applications

Physical

Chemical Properties

Equivalent

945 GPa 13700 ksi

00000400 ohm-cm 00000400 ohm-cm

000000134 000000134 cgsg

Thermal Properties

Component

Elements Properties

bcc gt 870AcircdegC

CHAPTER-3DESIGN

OVERVIEW

31 CMM DATA

THE BLADE

SURFACE

sections

283450000 0000000000 -100000000

283450000 0000000000 0000000000

283450000 0000000000 1000000000

28345-574-2292

28345-523-2325

28345-446-2336

28345-343-2322

28345-215-2282

28345-066-2212

28345 103-2111

28345 285-1972

28345 474-1791

28345 661-1562

28345 832-1278

28345 966-939

28345 104-553

28345 1035-143

44265 1521-1551

44265 1564-1521

44265 1581-1469

44265 1574-1395

44265 1544-1299

44265 1491-1183

44265 1419-1049

44265 1326-899

44265 1214-736

44265 1079-566

44265 923-395

44265 0 -100

44265 0 0

44265 0 100

32 LAYER OVER VIEW

Fig31 Single Blade

MERIDIONAL PROFILES

General

Ruled Element

Axial Element

General

Ruled Element

Axial Element

Blade Settings

Blade-to-Blade View

3D View

Blade-To-Blade View

3d View

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

11 INTRODUCTION

STEAM TURBINE-

BLADE-

material used

blades

machine as follows

2 LENGTH CUTTING

3 THICKNESS MILLING

6 RHOMBOID GRINDING

be within 8 microns

Program

12 CONCAVE MILLING

13 TAPER MILLING

DESIGN

PROPERTIES

Cast Iron

Physical Properties

0200 - 0282

lbinAcircsup3

Hardness Brinell

Hardness Knoop

Hardness Rockwell B

Hardness Rockwell C

Hardness Vickers

118 - 1650 MPa

17100 - 240000 psi

655 - 1450 MPa

9500 - 210000 psi

Elongation at Break

100 - 250 100 - 250

Reduction of Area

200 - 100 200 - 100

621 - 240 GPa 9000 - 34800 ksi

248 - 655 MPa 36000 - 95000 psi

331 - 2520 MPa

48000 - 365000 psi

Poissons Ratio

0240 - 0370 0240 - 0370

Fatigue Strength

689 - 510 MPa

10000 - 74000 psi

Fracture Toughness

Machinability

0000 - 125 0000 - 125

Shear Modulus

270 - 676 GPa

3920 - 9800 ksi

Shear Strength

149 - 1480 MPa

21600 - 215000 psi

400 - 244 J 295 - 180 ft-lb

407 - 123 J 300 - 910 ft-lb

000000500 - 110 ohm-cm

000000500 - 110

ohm-cm

Thermal

AcircdegF

113 - 533 Wm-K

784 - 370 BTU-inhr-

Melting Point

Shrinkage 0800 - 150 0800 - 150

Zirconium Zr

Characteristics

Applications

Physical

Chemical Properties

Equivalent

945 GPa 13700 ksi

00000400 ohm-cm 00000400 ohm-cm

000000134 000000134 cgsg

Thermal Properties

Component

Elements Properties

bcc gt 870AcircdegC

CHAPTER-3DESIGN

OVERVIEW

31 CMM DATA

THE BLADE

SURFACE

sections

283450000 0000000000 -100000000

283450000 0000000000 0000000000

283450000 0000000000 1000000000

28345-574-2292

28345-523-2325

28345-446-2336

28345-343-2322

28345-215-2282

28345-066-2212

28345 103-2111

28345 285-1972

28345 474-1791

28345 661-1562

28345 832-1278

28345 966-939

28345 104-553

28345 1035-143

44265 1521-1551

44265 1564-1521

44265 1581-1469

44265 1574-1395

44265 1544-1299

44265 1491-1183

44265 1419-1049

44265 1326-899

44265 1214-736

44265 1079-566

44265 923-395

44265 0 -100

44265 0 0

44265 0 100

32 LAYER OVER VIEW

Fig31 Single Blade

MERIDIONAL PROFILES

General

Ruled Element

Axial Element

General

Ruled Element

Axial Element

Blade Settings

Blade-to-Blade View

3D View

Blade-To-Blade View

3d View

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

11 INTRODUCTION

STEAM TURBINE-

BLADE-

material used

blades

machine as follows

2 LENGTH CUTTING

3 THICKNESS MILLING

6 RHOMBOID GRINDING

be within 8 microns

Program

12 CONCAVE MILLING

13 TAPER MILLING

DESIGN

PROPERTIES

Cast Iron

Physical Properties

0200 - 0282

lbinAcircsup3

Hardness Brinell

Hardness Knoop

Hardness Rockwell B

Hardness Rockwell C

Hardness Vickers

118 - 1650 MPa

17100 - 240000 psi

655 - 1450 MPa

9500 - 210000 psi

Elongation at Break

100 - 250 100 - 250

Reduction of Area

200 - 100 200 - 100

621 - 240 GPa 9000 - 34800 ksi

248 - 655 MPa 36000 - 95000 psi

331 - 2520 MPa

48000 - 365000 psi

Poissons Ratio

0240 - 0370 0240 - 0370

Fatigue Strength

689 - 510 MPa

10000 - 74000 psi

Fracture Toughness

Machinability

0000 - 125 0000 - 125

Shear Modulus

270 - 676 GPa

3920 - 9800 ksi

Shear Strength

149 - 1480 MPa

21600 - 215000 psi

400 - 244 J 295 - 180 ft-lb

407 - 123 J 300 - 910 ft-lb

000000500 - 110 ohm-cm

000000500 - 110

ohm-cm

Thermal

AcircdegF

113 - 533 Wm-K

784 - 370 BTU-inhr-

Melting Point

Shrinkage 0800 - 150 0800 - 150

Zirconium Zr

Characteristics

Applications

Physical

Chemical Properties

Equivalent

945 GPa 13700 ksi

00000400 ohm-cm 00000400 ohm-cm

000000134 000000134 cgsg

Thermal Properties

Component

Elements Properties

bcc gt 870AcircdegC

CHAPTER-3DESIGN

OVERVIEW

31 CMM DATA

THE BLADE

SURFACE

sections

283450000 0000000000 -100000000

283450000 0000000000 0000000000

283450000 0000000000 1000000000

28345-574-2292

28345-523-2325

28345-446-2336

28345-343-2322

28345-215-2282

28345-066-2212

28345 103-2111

28345 285-1972

28345 474-1791

28345 661-1562

28345 832-1278

28345 966-939

28345 104-553

28345 1035-143

44265 1521-1551

44265 1564-1521

44265 1581-1469

44265 1574-1395

44265 1544-1299

44265 1491-1183

44265 1419-1049

44265 1326-899

44265 1214-736

44265 1079-566

44265 923-395

44265 0 -100

44265 0 0

44265 0 100

32 LAYER OVER VIEW

Fig31 Single Blade

MERIDIONAL PROFILES

General

Ruled Element

Axial Element

General

Ruled Element

Axial Element

Blade Settings

Blade-to-Blade View

3D View

Blade-To-Blade View

3d View

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

11 INTRODUCTION

STEAM TURBINE-

BLADE-

material used

blades

machine as follows

2 LENGTH CUTTING

3 THICKNESS MILLING

6 RHOMBOID GRINDING

be within 8 microns

Program

12 CONCAVE MILLING

13 TAPER MILLING

DESIGN

PROPERTIES

Cast Iron

Physical Properties

0200 - 0282

lbinAcircsup3

Hardness Brinell

Hardness Knoop

Hardness Rockwell B

Hardness Rockwell C

Hardness Vickers

118 - 1650 MPa

17100 - 240000 psi

655 - 1450 MPa

9500 - 210000 psi

Elongation at Break

100 - 250 100 - 250

Reduction of Area

200 - 100 200 - 100

621 - 240 GPa 9000 - 34800 ksi

248 - 655 MPa 36000 - 95000 psi

331 - 2520 MPa

48000 - 365000 psi

Poissons Ratio

0240 - 0370 0240 - 0370

Fatigue Strength

689 - 510 MPa

10000 - 74000 psi

Fracture Toughness

Machinability

0000 - 125 0000 - 125

Shear Modulus

270 - 676 GPa

3920 - 9800 ksi

Shear Strength

149 - 1480 MPa

21600 - 215000 psi

400 - 244 J 295 - 180 ft-lb

407 - 123 J 300 - 910 ft-lb

000000500 - 110 ohm-cm

000000500 - 110

ohm-cm

Thermal

AcircdegF

113 - 533 Wm-K

784 - 370 BTU-inhr-

Melting Point

Shrinkage 0800 - 150 0800 - 150

Zirconium Zr

Characteristics

Applications

Physical

Chemical Properties

Equivalent

945 GPa 13700 ksi

00000400 ohm-cm 00000400 ohm-cm

000000134 000000134 cgsg

Thermal Properties

Component

Elements Properties

bcc gt 870AcircdegC

CHAPTER-3DESIGN

OVERVIEW

31 CMM DATA

THE BLADE

SURFACE

sections

283450000 0000000000 -100000000

283450000 0000000000 0000000000

283450000 0000000000 1000000000

28345-574-2292

28345-523-2325

28345-446-2336

28345-343-2322

28345-215-2282

28345-066-2212

28345 103-2111

28345 285-1972

28345 474-1791

28345 661-1562

28345 832-1278

28345 966-939

28345 104-553

28345 1035-143

44265 1521-1551

44265 1564-1521

44265 1581-1469

44265 1574-1395

44265 1544-1299

44265 1491-1183

44265 1419-1049

44265 1326-899

44265 1214-736

44265 1079-566

44265 923-395

44265 0 -100

44265 0 0

44265 0 100

32 LAYER OVER VIEW

Fig31 Single Blade

MERIDIONAL PROFILES

General

Ruled Element

Axial Element

General

Ruled Element

Axial Element

Blade Settings

Blade-to-Blade View

3D View

Blade-To-Blade View

3d View

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

blades

machine as follows

2 LENGTH CUTTING

3 THICKNESS MILLING

6 RHOMBOID GRINDING

be within 8 microns

Program

12 CONCAVE MILLING

13 TAPER MILLING

DESIGN

PROPERTIES

Cast Iron

Physical Properties

0200 - 0282

lbinAcircsup3

Hardness Brinell

Hardness Knoop

Hardness Rockwell B

Hardness Rockwell C

Hardness Vickers

118 - 1650 MPa

17100 - 240000 psi

655 - 1450 MPa

9500 - 210000 psi

Elongation at Break

100 - 250 100 - 250

Reduction of Area

200 - 100 200 - 100

621 - 240 GPa 9000 - 34800 ksi

248 - 655 MPa 36000 - 95000 psi

331 - 2520 MPa

48000 - 365000 psi

Poissons Ratio

0240 - 0370 0240 - 0370

Fatigue Strength

689 - 510 MPa

10000 - 74000 psi

Fracture Toughness

Machinability

0000 - 125 0000 - 125

Shear Modulus

270 - 676 GPa

3920 - 9800 ksi

Shear Strength

149 - 1480 MPa

21600 - 215000 psi

400 - 244 J 295 - 180 ft-lb

407 - 123 J 300 - 910 ft-lb

000000500 - 110 ohm-cm

000000500 - 110

ohm-cm

Thermal

AcircdegF

113 - 533 Wm-K

784 - 370 BTU-inhr-

Melting Point

Shrinkage 0800 - 150 0800 - 150

Zirconium Zr

Characteristics

Applications

Physical

Chemical Properties

Equivalent

945 GPa 13700 ksi

00000400 ohm-cm 00000400 ohm-cm

000000134 000000134 cgsg

Thermal Properties

Component

Elements Properties

bcc gt 870AcircdegC

CHAPTER-3DESIGN

OVERVIEW

31 CMM DATA

THE BLADE

SURFACE

sections

283450000 0000000000 -100000000

283450000 0000000000 0000000000

283450000 0000000000 1000000000

28345-574-2292

28345-523-2325

28345-446-2336

28345-343-2322

28345-215-2282

28345-066-2212

28345 103-2111

28345 285-1972

28345 474-1791

28345 661-1562

28345 832-1278

28345 966-939

28345 104-553

28345 1035-143

44265 1521-1551

44265 1564-1521

44265 1581-1469

44265 1574-1395

44265 1544-1299

44265 1491-1183

44265 1419-1049

44265 1326-899

44265 1214-736

44265 1079-566

44265 923-395

44265 0 -100

44265 0 0

44265 0 100

32 LAYER OVER VIEW

Fig31 Single Blade

MERIDIONAL PROFILES

General

Ruled Element

Axial Element

General

Ruled Element

Axial Element

Blade Settings

Blade-to-Blade View

3D View

Blade-To-Blade View

3d View

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

be within 8 microns

Program

12 CONCAVE MILLING

13 TAPER MILLING

DESIGN

PROPERTIES

Cast Iron

Physical Properties

0200 - 0282

lbinAcircsup3

Hardness Brinell

Hardness Knoop

Hardness Rockwell B

Hardness Rockwell C

Hardness Vickers

118 - 1650 MPa

17100 - 240000 psi

655 - 1450 MPa

9500 - 210000 psi

Elongation at Break

100 - 250 100 - 250

Reduction of Area

200 - 100 200 - 100

621 - 240 GPa 9000 - 34800 ksi

248 - 655 MPa 36000 - 95000 psi

331 - 2520 MPa

48000 - 365000 psi

Poissons Ratio

0240 - 0370 0240 - 0370

Fatigue Strength

689 - 510 MPa

10000 - 74000 psi

Fracture Toughness

Machinability

0000 - 125 0000 - 125

Shear Modulus

270 - 676 GPa

3920 - 9800 ksi

Shear Strength

149 - 1480 MPa

21600 - 215000 psi

400 - 244 J 295 - 180 ft-lb

407 - 123 J 300 - 910 ft-lb

000000500 - 110 ohm-cm

000000500 - 110

ohm-cm

Thermal

AcircdegF

113 - 533 Wm-K

784 - 370 BTU-inhr-

Melting Point

Shrinkage 0800 - 150 0800 - 150

Zirconium Zr

Characteristics

Applications

Physical

Chemical Properties

Equivalent

945 GPa 13700 ksi

00000400 ohm-cm 00000400 ohm-cm

000000134 000000134 cgsg

Thermal Properties

Component

Elements Properties

bcc gt 870AcircdegC

CHAPTER-3DESIGN

OVERVIEW

31 CMM DATA

THE BLADE

SURFACE

sections

283450000 0000000000 -100000000

283450000 0000000000 0000000000

283450000 0000000000 1000000000

28345-574-2292

28345-523-2325

28345-446-2336

28345-343-2322

28345-215-2282

28345-066-2212

28345 103-2111

28345 285-1972

28345 474-1791

28345 661-1562

28345 832-1278

28345 966-939

28345 104-553

28345 1035-143

44265 1521-1551

44265 1564-1521

44265 1581-1469

44265 1574-1395

44265 1544-1299

44265 1491-1183

44265 1419-1049

44265 1326-899

44265 1214-736

44265 1079-566

44265 923-395

44265 0 -100

44265 0 0

44265 0 100

32 LAYER OVER VIEW

Fig31 Single Blade

MERIDIONAL PROFILES

General

Ruled Element

Axial Element

General

Ruled Element

Axial Element

Blade Settings

Blade-to-Blade View

3D View

Blade-To-Blade View

3d View

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

DESIGN

PROPERTIES

Cast Iron

Physical Properties

0200 - 0282

lbinAcircsup3

Hardness Brinell

Hardness Knoop

Hardness Rockwell B

Hardness Rockwell C

Hardness Vickers

118 - 1650 MPa

17100 - 240000 psi

655 - 1450 MPa

9500 - 210000 psi

Elongation at Break

100 - 250 100 - 250

Reduction of Area

200 - 100 200 - 100

621 - 240 GPa 9000 - 34800 ksi

248 - 655 MPa 36000 - 95000 psi

331 - 2520 MPa

48000 - 365000 psi

Poissons Ratio

0240 - 0370 0240 - 0370

Fatigue Strength

689 - 510 MPa

10000 - 74000 psi

Fracture Toughness

Machinability

0000 - 125 0000 - 125

Shear Modulus

270 - 676 GPa

3920 - 9800 ksi

Shear Strength

149 - 1480 MPa

21600 - 215000 psi

400 - 244 J 295 - 180 ft-lb

407 - 123 J 300 - 910 ft-lb

000000500 - 110 ohm-cm

000000500 - 110

ohm-cm

Thermal

AcircdegF

113 - 533 Wm-K

784 - 370 BTU-inhr-

Melting Point

Shrinkage 0800 - 150 0800 - 150

Zirconium Zr

Characteristics

Applications

Physical

Chemical Properties

Equivalent

945 GPa 13700 ksi

00000400 ohm-cm 00000400 ohm-cm

000000134 000000134 cgsg

Thermal Properties

Component

Elements Properties

bcc gt 870AcircdegC

CHAPTER-3DESIGN

OVERVIEW

31 CMM DATA

THE BLADE

SURFACE

sections

283450000 0000000000 -100000000

283450000 0000000000 0000000000

283450000 0000000000 1000000000

28345-574-2292

28345-523-2325

28345-446-2336

28345-343-2322

28345-215-2282

28345-066-2212

28345 103-2111

28345 285-1972

28345 474-1791

28345 661-1562

28345 832-1278

28345 966-939

28345 104-553

28345 1035-143

44265 1521-1551

44265 1564-1521

44265 1581-1469

44265 1574-1395

44265 1544-1299

44265 1491-1183

44265 1419-1049

44265 1326-899

44265 1214-736

44265 1079-566

44265 923-395

44265 0 -100

44265 0 0

44265 0 100

32 LAYER OVER VIEW

Fig31 Single Blade

MERIDIONAL PROFILES

General

Ruled Element

Axial Element

General

Ruled Element

Axial Element

Blade Settings

Blade-to-Blade View

3D View

Blade-To-Blade View

3d View

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

DESIGN

PROPERTIES

Cast Iron

Physical Properties

0200 - 0282

lbinAcircsup3

Hardness Brinell

Hardness Knoop

Hardness Rockwell B

Hardness Rockwell C

Hardness Vickers

118 - 1650 MPa

17100 - 240000 psi

655 - 1450 MPa

9500 - 210000 psi

Elongation at Break

100 - 250 100 - 250

Reduction of Area

200 - 100 200 - 100

621 - 240 GPa 9000 - 34800 ksi

248 - 655 MPa 36000 - 95000 psi

331 - 2520 MPa

48000 - 365000 psi

Poissons Ratio

0240 - 0370 0240 - 0370

Fatigue Strength

689 - 510 MPa

10000 - 74000 psi

Fracture Toughness

Machinability

0000 - 125 0000 - 125

Shear Modulus

270 - 676 GPa

3920 - 9800 ksi

Shear Strength

149 - 1480 MPa

21600 - 215000 psi

400 - 244 J 295 - 180 ft-lb

407 - 123 J 300 - 910 ft-lb

000000500 - 110 ohm-cm

000000500 - 110

ohm-cm

Thermal

AcircdegF

113 - 533 Wm-K

784 - 370 BTU-inhr-

Melting Point

Shrinkage 0800 - 150 0800 - 150

Zirconium Zr

Characteristics

Applications

Physical

Chemical Properties

Equivalent

945 GPa 13700 ksi

00000400 ohm-cm 00000400 ohm-cm

000000134 000000134 cgsg

Thermal Properties

Component

Elements Properties

bcc gt 870AcircdegC

CHAPTER-3DESIGN

OVERVIEW

31 CMM DATA

THE BLADE

SURFACE

sections

283450000 0000000000 -100000000

283450000 0000000000 0000000000

283450000 0000000000 1000000000

28345-574-2292

28345-523-2325

28345-446-2336

28345-343-2322

28345-215-2282

28345-066-2212

28345 103-2111

28345 285-1972

28345 474-1791

28345 661-1562

28345 832-1278

28345 966-939

28345 104-553

28345 1035-143

44265 1521-1551

44265 1564-1521

44265 1581-1469

44265 1574-1395

44265 1544-1299

44265 1491-1183

44265 1419-1049

44265 1326-899

44265 1214-736

44265 1079-566

44265 923-395

44265 0 -100

44265 0 0

44265 0 100

32 LAYER OVER VIEW

Fig31 Single Blade

MERIDIONAL PROFILES

General

Ruled Element

Axial Element

General

Ruled Element

Axial Element

Blade Settings

Blade-to-Blade View

3D View

Blade-To-Blade View

3d View

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

DESIGN

PROPERTIES

Cast Iron

Physical Properties

0200 - 0282

lbinAcircsup3

Hardness Brinell

Hardness Knoop

Hardness Rockwell B

Hardness Rockwell C

Hardness Vickers

118 - 1650 MPa

17100 - 240000 psi

655 - 1450 MPa

9500 - 210000 psi

Elongation at Break

100 - 250 100 - 250

Reduction of Area

200 - 100 200 - 100

621 - 240 GPa 9000 - 34800 ksi

248 - 655 MPa 36000 - 95000 psi

331 - 2520 MPa

48000 - 365000 psi

Poissons Ratio

0240 - 0370 0240 - 0370

Fatigue Strength

689 - 510 MPa

10000 - 74000 psi

Fracture Toughness

Machinability

0000 - 125 0000 - 125

Shear Modulus

270 - 676 GPa

3920 - 9800 ksi

Shear Strength

149 - 1480 MPa

21600 - 215000 psi

400 - 244 J 295 - 180 ft-lb

407 - 123 J 300 - 910 ft-lb

000000500 - 110 ohm-cm

000000500 - 110

ohm-cm

Thermal

AcircdegF

113 - 533 Wm-K

784 - 370 BTU-inhr-

Melting Point

Shrinkage 0800 - 150 0800 - 150

Zirconium Zr

Characteristics

Applications

Physical

Chemical Properties

Equivalent

945 GPa 13700 ksi

00000400 ohm-cm 00000400 ohm-cm

000000134 000000134 cgsg

Thermal Properties

Component

Elements Properties

bcc gt 870AcircdegC

CHAPTER-3DESIGN

OVERVIEW

31 CMM DATA

THE BLADE

SURFACE

sections

283450000 0000000000 -100000000

283450000 0000000000 0000000000

283450000 0000000000 1000000000

28345-574-2292

28345-523-2325

28345-446-2336

28345-343-2322

28345-215-2282

28345-066-2212

28345 103-2111

28345 285-1972

28345 474-1791

28345 661-1562

28345 832-1278

28345 966-939

28345 104-553

28345 1035-143

44265 1521-1551

44265 1564-1521

44265 1581-1469

44265 1574-1395

44265 1544-1299

44265 1491-1183

44265 1419-1049

44265 1326-899

44265 1214-736

44265 1079-566

44265 923-395

44265 0 -100

44265 0 0

44265 0 100

32 LAYER OVER VIEW

Fig31 Single Blade

MERIDIONAL PROFILES

General

Ruled Element

Axial Element

General

Ruled Element

Axial Element

Blade Settings

Blade-to-Blade View

3D View

Blade-To-Blade View

3d View

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

DESIGN

PROPERTIES

Cast Iron

Physical Properties

0200 - 0282

lbinAcircsup3

Hardness Brinell

Hardness Knoop

Hardness Rockwell B

Hardness Rockwell C

Hardness Vickers

118 - 1650 MPa

17100 - 240000 psi

655 - 1450 MPa

9500 - 210000 psi

Elongation at Break

100 - 250 100 - 250

Reduction of Area

200 - 100 200 - 100

621 - 240 GPa 9000 - 34800 ksi

248 - 655 MPa 36000 - 95000 psi

331 - 2520 MPa

48000 - 365000 psi

Poissons Ratio

0240 - 0370 0240 - 0370

Fatigue Strength

689 - 510 MPa

10000 - 74000 psi

Fracture Toughness

Machinability

0000 - 125 0000 - 125

Shear Modulus

270 - 676 GPa

3920 - 9800 ksi

Shear Strength

149 - 1480 MPa

21600 - 215000 psi

400 - 244 J 295 - 180 ft-lb

407 - 123 J 300 - 910 ft-lb

000000500 - 110 ohm-cm

000000500 - 110

ohm-cm

Thermal

AcircdegF

113 - 533 Wm-K

784 - 370 BTU-inhr-

Melting Point

Shrinkage 0800 - 150 0800 - 150

Zirconium Zr

Characteristics

Applications

Physical

Chemical Properties

Equivalent

945 GPa 13700 ksi

00000400 ohm-cm 00000400 ohm-cm

000000134 000000134 cgsg

Thermal Properties

Component

Elements Properties

bcc gt 870AcircdegC

CHAPTER-3DESIGN

OVERVIEW

31 CMM DATA

THE BLADE

SURFACE

sections

283450000 0000000000 -100000000

283450000 0000000000 0000000000

283450000 0000000000 1000000000

28345-574-2292

28345-523-2325

28345-446-2336

28345-343-2322

28345-215-2282

28345-066-2212

28345 103-2111

28345 285-1972

28345 474-1791

28345 661-1562

28345 832-1278

28345 966-939

28345 104-553

28345 1035-143

44265 1521-1551

44265 1564-1521

44265 1581-1469

44265 1574-1395

44265 1544-1299

44265 1491-1183

44265 1419-1049

44265 1326-899

44265 1214-736

44265 1079-566

44265 923-395

44265 0 -100

44265 0 0

44265 0 100

32 LAYER OVER VIEW

Fig31 Single Blade

MERIDIONAL PROFILES

General

Ruled Element

Axial Element

General

Ruled Element

Axial Element

Blade Settings

Blade-to-Blade View

3D View

Blade-To-Blade View

3d View

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

PROPERTIES

Cast Iron

Physical Properties

0200 - 0282

lbinAcircsup3

Hardness Brinell

Hardness Knoop

Hardness Rockwell B

Hardness Rockwell C

Hardness Vickers

118 - 1650 MPa

17100 - 240000 psi

655 - 1450 MPa

9500 - 210000 psi

Elongation at Break

100 - 250 100 - 250

Reduction of Area

200 - 100 200 - 100

621 - 240 GPa 9000 - 34800 ksi

248 - 655 MPa 36000 - 95000 psi

331 - 2520 MPa

48000 - 365000 psi

Poissons Ratio

0240 - 0370 0240 - 0370

Fatigue Strength

689 - 510 MPa

10000 - 74000 psi

Fracture Toughness

Machinability

0000 - 125 0000 - 125

Shear Modulus

270 - 676 GPa

3920 - 9800 ksi

Shear Strength

149 - 1480 MPa

21600 - 215000 psi

400 - 244 J 295 - 180 ft-lb

407 - 123 J 300 - 910 ft-lb

000000500 - 110 ohm-cm

000000500 - 110

ohm-cm

Thermal

AcircdegF

113 - 533 Wm-K

784 - 370 BTU-inhr-

Melting Point

Shrinkage 0800 - 150 0800 - 150

Zirconium Zr

Characteristics

Applications

Physical

Chemical Properties

Equivalent

945 GPa 13700 ksi

00000400 ohm-cm 00000400 ohm-cm

000000134 000000134 cgsg

Thermal Properties

Component

Elements Properties

bcc gt 870AcircdegC

CHAPTER-3DESIGN

OVERVIEW

31 CMM DATA

THE BLADE

SURFACE

sections

283450000 0000000000 -100000000

283450000 0000000000 0000000000

283450000 0000000000 1000000000

28345-574-2292

28345-523-2325

28345-446-2336

28345-343-2322

28345-215-2282

28345-066-2212

28345 103-2111

28345 285-1972

28345 474-1791

28345 661-1562

28345 832-1278

28345 966-939

28345 104-553

28345 1035-143

44265 1521-1551

44265 1564-1521

44265 1581-1469

44265 1574-1395

44265 1544-1299

44265 1491-1183

44265 1419-1049

44265 1326-899

44265 1214-736

44265 1079-566

44265 923-395

44265 0 -100

44265 0 0

44265 0 100

32 LAYER OVER VIEW

Fig31 Single Blade

MERIDIONAL PROFILES

General

Ruled Element

Axial Element

General

Ruled Element

Axial Element

Blade Settings

Blade-to-Blade View

3D View

Blade-To-Blade View

3d View

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

PROPERTIES

Cast Iron

Physical Properties

0200 - 0282

lbinAcircsup3

Hardness Brinell

Hardness Knoop

Hardness Rockwell B

Hardness Rockwell C

Hardness Vickers

118 - 1650 MPa

17100 - 240000 psi

655 - 1450 MPa

9500 - 210000 psi

Elongation at Break

100 - 250 100 - 250

Reduction of Area

200 - 100 200 - 100

621 - 240 GPa 9000 - 34800 ksi

248 - 655 MPa 36000 - 95000 psi

331 - 2520 MPa

48000 - 365000 psi

Poissons Ratio

0240 - 0370 0240 - 0370

Fatigue Strength

689 - 510 MPa

10000 - 74000 psi

Fracture Toughness

Machinability

0000 - 125 0000 - 125

Shear Modulus

270 - 676 GPa

3920 - 9800 ksi

Shear Strength

149 - 1480 MPa

21600 - 215000 psi

400 - 244 J 295 - 180 ft-lb

407 - 123 J 300 - 910 ft-lb

000000500 - 110 ohm-cm

000000500 - 110

ohm-cm

Thermal

AcircdegF

113 - 533 Wm-K

784 - 370 BTU-inhr-

Melting Point

Shrinkage 0800 - 150 0800 - 150

Zirconium Zr

Characteristics

Applications

Physical

Chemical Properties

Equivalent

945 GPa 13700 ksi

00000400 ohm-cm 00000400 ohm-cm

000000134 000000134 cgsg

Thermal Properties

Component

Elements Properties

bcc gt 870AcircdegC

CHAPTER-3DESIGN

OVERVIEW

31 CMM DATA

THE BLADE

SURFACE

sections

283450000 0000000000 -100000000

283450000 0000000000 0000000000

283450000 0000000000 1000000000

28345-574-2292

28345-523-2325

28345-446-2336

28345-343-2322

28345-215-2282

28345-066-2212

28345 103-2111

28345 285-1972

28345 474-1791

28345 661-1562

28345 832-1278

28345 966-939

28345 104-553

28345 1035-143

44265 1521-1551

44265 1564-1521

44265 1581-1469

44265 1574-1395

44265 1544-1299

44265 1491-1183

44265 1419-1049

44265 1326-899

44265 1214-736

44265 1079-566

44265 923-395

44265 0 -100

44265 0 0

44265 0 100

32 LAYER OVER VIEW

Fig31 Single Blade

MERIDIONAL PROFILES

General

Ruled Element

Axial Element

General

Ruled Element

Axial Element

Blade Settings

Blade-to-Blade View

3D View

Blade-To-Blade View

3d View

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

Hardness Brinell

Hardness Knoop

Hardness Rockwell B

Hardness Rockwell C

Hardness Vickers

118 - 1650 MPa

17100 - 240000 psi

655 - 1450 MPa

9500 - 210000 psi

Elongation at Break

100 - 250 100 - 250

Reduction of Area

200 - 100 200 - 100

621 - 240 GPa 9000 - 34800 ksi

248 - 655 MPa 36000 - 95000 psi

331 - 2520 MPa

48000 - 365000 psi

Poissons Ratio

0240 - 0370 0240 - 0370

Fatigue Strength

689 - 510 MPa

10000 - 74000 psi

Fracture Toughness

Machinability

0000 - 125 0000 - 125

Shear Modulus

270 - 676 GPa

3920 - 9800 ksi

Shear Strength

149 - 1480 MPa

21600 - 215000 psi

400 - 244 J 295 - 180 ft-lb

407 - 123 J 300 - 910 ft-lb

000000500 - 110 ohm-cm

000000500 - 110

ohm-cm

Thermal

AcircdegF

113 - 533 Wm-K

784 - 370 BTU-inhr-

Melting Point

Shrinkage 0800 - 150 0800 - 150

Zirconium Zr

Characteristics

Applications

Physical

Chemical Properties

Equivalent

945 GPa 13700 ksi

00000400 ohm-cm 00000400 ohm-cm

000000134 000000134 cgsg

Thermal Properties

Component

Elements Properties

bcc gt 870AcircdegC

CHAPTER-3DESIGN

OVERVIEW

31 CMM DATA

THE BLADE

SURFACE

sections

283450000 0000000000 -100000000

283450000 0000000000 0000000000

283450000 0000000000 1000000000

28345-574-2292

28345-523-2325

28345-446-2336

28345-343-2322

28345-215-2282

28345-066-2212

28345 103-2111

28345 285-1972

28345 474-1791

28345 661-1562

28345 832-1278

28345 966-939

28345 104-553

28345 1035-143

44265 1521-1551

44265 1564-1521

44265 1581-1469

44265 1574-1395

44265 1544-1299

44265 1491-1183

44265 1419-1049

44265 1326-899

44265 1214-736

44265 1079-566

44265 923-395

44265 0 -100

44265 0 0

44265 0 100

32 LAYER OVER VIEW

Fig31 Single Blade

MERIDIONAL PROFILES

General

Ruled Element

Axial Element

General

Ruled Element

Axial Element

Blade Settings

Blade-to-Blade View

3D View

Blade-To-Blade View

3d View

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

407 - 123 J 300 - 910 ft-lb

000000500 - 110 ohm-cm

000000500 - 110

ohm-cm

Thermal

AcircdegF

113 - 533 Wm-K

784 - 370 BTU-inhr-

Melting Point

Shrinkage 0800 - 150 0800 - 150

Zirconium Zr

Characteristics

Applications

Physical

Chemical Properties

Equivalent

945 GPa 13700 ksi

00000400 ohm-cm 00000400 ohm-cm

000000134 000000134 cgsg

Thermal Properties

Component

Elements Properties

bcc gt 870AcircdegC

CHAPTER-3DESIGN

OVERVIEW

31 CMM DATA

THE BLADE

SURFACE

sections

283450000 0000000000 -100000000

283450000 0000000000 0000000000

283450000 0000000000 1000000000

28345-574-2292

28345-523-2325

28345-446-2336

28345-343-2322

28345-215-2282

28345-066-2212

28345 103-2111

28345 285-1972

28345 474-1791

28345 661-1562

28345 832-1278

28345 966-939

28345 104-553

28345 1035-143

44265 1521-1551

44265 1564-1521

44265 1581-1469

44265 1574-1395

44265 1544-1299

44265 1491-1183

44265 1419-1049

44265 1326-899

44265 1214-736

44265 1079-566

44265 923-395

44265 0 -100

44265 0 0

44265 0 100

32 LAYER OVER VIEW

Fig31 Single Blade

MERIDIONAL PROFILES

General

Ruled Element

Axial Element

General

Ruled Element

Axial Element

Blade Settings

Blade-to-Blade View

3D View

Blade-To-Blade View

3d View

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

Zirconium Zr

Characteristics

Applications

Physical

Chemical Properties

Equivalent

945 GPa 13700 ksi

00000400 ohm-cm 00000400 ohm-cm

000000134 000000134 cgsg

Thermal Properties

Component

Elements Properties

bcc gt 870AcircdegC

CHAPTER-3DESIGN

OVERVIEW

31 CMM DATA

THE BLADE

SURFACE

sections

283450000 0000000000 -100000000

283450000 0000000000 0000000000

283450000 0000000000 1000000000

28345-574-2292

28345-523-2325

28345-446-2336

28345-343-2322

28345-215-2282

28345-066-2212

28345 103-2111

28345 285-1972

28345 474-1791

28345 661-1562

28345 832-1278

28345 966-939

28345 104-553

28345 1035-143

44265 1521-1551

44265 1564-1521

44265 1581-1469

44265 1574-1395

44265 1544-1299

44265 1491-1183

44265 1419-1049

44265 1326-899

44265 1214-736

44265 1079-566

44265 923-395

44265 0 -100

44265 0 0

44265 0 100

32 LAYER OVER VIEW

Fig31 Single Blade

MERIDIONAL PROFILES

General

Ruled Element

Axial Element

General

Ruled Element

Axial Element

Blade Settings

Blade-to-Blade View

3D View

Blade-To-Blade View

3d View

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

Chemical Properties

Equivalent

945 GPa 13700 ksi

00000400 ohm-cm 00000400 ohm-cm

000000134 000000134 cgsg

Thermal Properties

Component

Elements Properties

bcc gt 870AcircdegC

CHAPTER-3DESIGN

OVERVIEW

31 CMM DATA

THE BLADE

SURFACE

sections

283450000 0000000000 -100000000

283450000 0000000000 0000000000

283450000 0000000000 1000000000

28345-574-2292

28345-523-2325

28345-446-2336

28345-343-2322

28345-215-2282

28345-066-2212

28345 103-2111

28345 285-1972

28345 474-1791

28345 661-1562

28345 832-1278

28345 966-939

28345 104-553

28345 1035-143

44265 1521-1551

44265 1564-1521

44265 1581-1469

44265 1574-1395

44265 1544-1299

44265 1491-1183

44265 1419-1049

44265 1326-899

44265 1214-736

44265 1079-566

44265 923-395

44265 0 -100

44265 0 0

44265 0 100

32 LAYER OVER VIEW

Fig31 Single Blade

MERIDIONAL PROFILES

General

Ruled Element

Axial Element

General

Ruled Element

Axial Element

Blade Settings

Blade-to-Blade View

3D View

Blade-To-Blade View

3d View

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

Equivalent

945 GPa 13700 ksi

00000400 ohm-cm 00000400 ohm-cm

000000134 000000134 cgsg

Thermal Properties

Component

Elements Properties

bcc gt 870AcircdegC

CHAPTER-3DESIGN

OVERVIEW

31 CMM DATA

THE BLADE

SURFACE

sections

283450000 0000000000 -100000000

283450000 0000000000 0000000000

283450000 0000000000 1000000000

28345-574-2292

28345-523-2325

28345-446-2336

28345-343-2322

28345-215-2282

28345-066-2212

28345 103-2111

28345 285-1972

28345 474-1791

28345 661-1562

28345 832-1278

28345 966-939

28345 104-553

28345 1035-143

44265 1521-1551

44265 1564-1521

44265 1581-1469

44265 1574-1395

44265 1544-1299

44265 1491-1183

44265 1419-1049

44265 1326-899

44265 1214-736

44265 1079-566

44265 923-395

44265 0 -100

44265 0 0

44265 0 100

32 LAYER OVER VIEW

Fig31 Single Blade

MERIDIONAL PROFILES

General

Ruled Element

Axial Element

General

Ruled Element

Axial Element

Blade Settings

Blade-to-Blade View

3D View

Blade-To-Blade View

3d View

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

Thermal Properties

Component

Elements Properties

bcc gt 870AcircdegC

CHAPTER-3DESIGN

OVERVIEW

31 CMM DATA

THE BLADE

SURFACE

sections

283450000 0000000000 -100000000

283450000 0000000000 0000000000

283450000 0000000000 1000000000

28345-574-2292

28345-523-2325

28345-446-2336

28345-343-2322

28345-215-2282

28345-066-2212

28345 103-2111

28345 285-1972

28345 474-1791

28345 661-1562

28345 832-1278

28345 966-939

28345 104-553

28345 1035-143

44265 1521-1551

44265 1564-1521

44265 1581-1469

44265 1574-1395

44265 1544-1299

44265 1491-1183

44265 1419-1049

44265 1326-899

44265 1214-736

44265 1079-566

44265 923-395

44265 0 -100

44265 0 0

44265 0 100

32 LAYER OVER VIEW

Fig31 Single Blade

MERIDIONAL PROFILES

General

Ruled Element

Axial Element

General

Ruled Element

Axial Element

Blade Settings

Blade-to-Blade View

3D View

Blade-To-Blade View

3d View

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

bcc gt 870AcircdegC

CHAPTER-3DESIGN

OVERVIEW

31 CMM DATA

THE BLADE

SURFACE

sections

283450000 0000000000 -100000000

283450000 0000000000 0000000000

283450000 0000000000 1000000000

28345-574-2292

28345-523-2325

28345-446-2336

28345-343-2322

28345-215-2282

28345-066-2212

28345 103-2111

28345 285-1972

28345 474-1791

28345 661-1562

28345 832-1278

28345 966-939

28345 104-553

28345 1035-143

44265 1521-1551

44265 1564-1521

44265 1581-1469

44265 1574-1395

44265 1544-1299

44265 1491-1183

44265 1419-1049

44265 1326-899

44265 1214-736

44265 1079-566

44265 923-395

44265 0 -100

44265 0 0

44265 0 100

32 LAYER OVER VIEW

Fig31 Single Blade

MERIDIONAL PROFILES

General

Ruled Element

Axial Element

General

Ruled Element

Axial Element

Blade Settings

Blade-to-Blade View

3D View

Blade-To-Blade View

3d View

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

31 CMM DATA

THE BLADE

SURFACE

sections

283450000 0000000000 -100000000

283450000 0000000000 0000000000

283450000 0000000000 1000000000

28345-574-2292

28345-523-2325

28345-446-2336

28345-343-2322

28345-215-2282

28345-066-2212

28345 103-2111

28345 285-1972

28345 474-1791

28345 661-1562

28345 832-1278

28345 966-939

28345 104-553

28345 1035-143

44265 1521-1551

44265 1564-1521

44265 1581-1469

44265 1574-1395

44265 1544-1299

44265 1491-1183

44265 1419-1049

44265 1326-899

44265 1214-736

44265 1079-566

44265 923-395

44265 0 -100

44265 0 0

44265 0 100

32 LAYER OVER VIEW

Fig31 Single Blade

MERIDIONAL PROFILES

General

Ruled Element

Axial Element

General

Ruled Element

Axial Element

Blade Settings

Blade-to-Blade View

3D View

Blade-To-Blade View

3d View

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

283450000 0000000000 -100000000

283450000 0000000000 0000000000

283450000 0000000000 1000000000

28345-574-2292

28345-523-2325

28345-446-2336

28345-343-2322

28345-215-2282

28345-066-2212

28345 103-2111

28345 285-1972

28345 474-1791

28345 661-1562

28345 832-1278

28345 966-939

28345 104-553

28345 1035-143

44265 1521-1551

44265 1564-1521

44265 1581-1469

44265 1574-1395

44265 1544-1299

44265 1491-1183

44265 1419-1049

44265 1326-899

44265 1214-736

44265 1079-566

44265 923-395

44265 0 -100

44265 0 0

44265 0 100

32 LAYER OVER VIEW

Fig31 Single Blade

MERIDIONAL PROFILES

General

Ruled Element

Axial Element

General

Ruled Element

Axial Element

Blade Settings

Blade-to-Blade View

3D View

Blade-To-Blade View

3d View

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

44265 1521-1551

44265 1564-1521

44265 1581-1469

44265 1574-1395

44265 1544-1299

44265 1491-1183

44265 1419-1049

44265 1326-899

44265 1214-736

44265 1079-566

44265 923-395

44265 0 -100

44265 0 0

44265 0 100

32 LAYER OVER VIEW

Fig31 Single Blade

MERIDIONAL PROFILES

General

Ruled Element

Axial Element

General

Ruled Element

Axial Element

Blade Settings

Blade-to-Blade View

3D View

Blade-To-Blade View

3d View

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

Fig31 Single Blade

MERIDIONAL PROFILES

General

Ruled Element

Axial Element

General

Ruled Element

Axial Element

Blade Settings

Blade-to-Blade View

3D View

Blade-To-Blade View

3d View

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

Ruled Element

Axial Element

Blade Settings

Blade-to-Blade View

3D View

Blade-To-Blade View

3d View

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

Blade Settings

Blade-to-Blade View

3D View

Blade-To-Blade View

3d View

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

3d View

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

OverUnder-Filing)

conventions

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

geometry

design objects

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

2D CAD

3D CAD

anymore

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

desired designs

manufacturability

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

PART DESIGN

ASSEMBLY

DRAWING

SKETCHER

35 DESIGN OVERVIEW

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

a rotating disc

Excessive stresses

frequencies

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

Excessive stress

importance

Centrifugal stress

upon them

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

Impact stress

the thrust bearing

Low cycle fatigue

Thermal fatigue

Creep stress

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

Resonant vibration

model was created

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

conditions

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

blades

blades together

solid modelrdquo

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

CHAPTER-4ANALYSIS

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

INTRODUCTION TO FEA

complex structures

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

the new condition

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

are shown

Rod elements

Beam elements

Shear panel

Solid elements

Spring elements

Mass elements

Rigid elements

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

diffusion

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

equations

prototyping

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

ANALYSISON

BLADES

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

RESULTS TABLE

1 Chrome Steel

2 Titanium

Stress(Nmm2) 33907 327817 258892

Displacement(mm) 0147608 0256561 0430927

715055 605119 72591

Thermal flux(Wmm2)

11727 10287 1597

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

Stress(Nmm2)

1 2 30

35033907 327817

258892

Displacement(mm)

1 2 30

0147608

0256561

00430927000000001

Displacement(mm)

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

Temperature(degc)

1 2 30

600 533 533 533

Temperature(degc)

1 2 30

8007150549999999

605119

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

Thermal flux(Wmm2)

1 2 30

1172710287

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

CHAPTER-6CONCLUSION

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

CONCLUSION

material

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

References

Vol-96 (20) pp 159-167

1990 volume 33 pp 501-505

Vol 240(5) pp 891-908

111 pp 610-618

2D CAD

3D CAD

Solid Modeling

Documents

Documentation(1) 2 2