MODELLING, STRUCTURAL ANALYSIS AND CFD FLUENT ANALYSIS OF HIGH SPEED GAS TURBINE · PDF file · 2017-09-25CFD FLUENT ANALYSIS OF HIGH SPEED GAS TURBINE BLADES ... Gas turbine blades,

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International Journal of Mechanical Engineering and Technology (IJMET) Volume 8, Issue 9, September 2017, pp. 77–85, Article ID: IJMET_08_09_008

Available online at http://www.iaeme.com/IJMET/issues.asp?JType=IJMET&VType=8&IType=9

ISSN Print: 0976-6340 and ISSN Online: 0976-6359

© IAEME Publication Scopus Indexed

MODELLING, STRUCTURAL ANALYSIS AND

CFD FLUENT ANALYSIS OF HIGH SPEED GAS

TURBINE BLADES

G. Ragul, Rituparna Biswas

Department of Mechanical Engineering, Budge Budge Institute of Technology,

Kolkata, West Bengal, India

C. Sreejith, G. Shaikh Usman Sha

Department of Mechanical Engineering, Nehru college of Engineering and Research Centre,

Thrissur, Kerala, India

V. Jayakumar

Department of Mechanical Engineering, Saveetha School of Engineering,

Saveetha University, Chennai, Tamil Nadu, India

ABSTRACT

This research paper investigates the improvement of the overall thermal efficiency

in high pressure and high temperature operation gas turbine at the high inlet

temperature. To develop design the gas turbine with minimal effect of the engine

thermal efficiency. In this numerical calculations between fluid and the thermal effect

is important in design considerations. In this work we considered two fluid domains

that hot gas flows in turbine and other coolant air flow over plenum, and in blade

itself as a solid domain meshed independently by using Ansys CFD meshing software.

Generalized grid interfaces (GGIs) were introduced to connect the non-matching

mesh topologies of individual domains. One dimensional simulations was connected to

Ansys using the standard, coolant air flow in plenum and the same time, CFD

simulation can be used as unique Ansys model for laminar to turbulent transition.

Keywords: Gas turbine blades, FEA modelling, Structural analysis, CFD fluent

analysis

Cite this Article: G. Ragul, Rituparna Biswas, C. Sreejith, G. Shaikh Usman Sha and

V. Jayakumar, Modelling, Structural Analysis And Cfd Fluent Analysis of High Speed

Gas Turbine Blades, International Journal of Mechanical Engineering and Technology

8(9), 2017, pp. 77–85.

http://www.iaeme.com/IJMET/issues.asp?JType=IJMET&VType=8&IType=9

Modelling, Structural Analysis and CFD Fluent Analysis of High Speed Gas Turbine Blades


1. INTRODUCTION

Generally in gas turbines, at the high temperature and pressure hot gas enters into the turbine

from the combustion system to the rotating turbine blades for the expansion process. In order

to increase the overall thermal efficiency as a result advanced gas turbines are used to

maximise the output. T. Sadowski, P. Golewski [1] introduced the concept of one method of

extracting air from the compressor by turbine blades and forces in to plenum and into channel

inside the blade. Kyung Min Kim, Jun Su Park et.al [2] investigated the heat transfer and the

overall structural stresses developed in gas turbine with circular cooling passages. Heeyoon

Chung and Jun Su Park [3] introduced the concept of heat transfer distribution on surfaces by

naphthalene sublimation method by using the correlation between heat and mass transfer.

Vlad Ganine, Umesh Javiya et.al [4] employed new strategy to estimate the heat transfer

coefficient and also lower fluid domain solver in reducing the cost of coupled aero-thermal

analysis. Igor V. Shevchuk, Sean C. Jenkins et.al [5] described the performance and life time

prediction of a high pressure turbine blade and also CHT method. Similarly several other

studies [6-10] have presented about improvement of the thermal efficiency of the advanced

gas turbine by change in the gas turbines and also chemical composition of materials.

2. RESEARCH METHODS

An aero-thermal analysis investigates the temperature of a turbine blade when coolant is

ejected from the trailing edge with a span wise component. An understanding of the way the

temperature varies under coolant flow conditions will be useful when applying analytical

methods to determine aerodynamic loss. The main objective to achieve these aims is to obtain

accurate coolant mass flow rates and coolant ejection. In order for temperature measurements

to be taken the central blade Table.1 shows the blade dimensions and Figure.1 shows the

specification of wind turbine. Figure.2 shows the sectional flow design and designed by Pro/E

commercial software.

Table 1: Blade specification

Number of blades 1

Chord length 140 mm

Pitch 105 mm

Pitch to chord ratio 0.75

Axial chord length 83 mm

Throat width 30 mm

Gauging angle 74°

Inlet flow angle 0°

Outlet flow angle 70°-78°

Stagger angle 51.9°

Span 454 mm

Trailing edge thickness 3.2 mm

G. Ragul, Rituparna Biswas, C. Sreejith, G. Shaikh Usman Sha and V. Jayakumar


Figure 1 Schematic diagram of turbine blade

Figure 2 Sectional flow view and design of wind turbine by Pro/E

Figure 3Turbine blade without internal passages as per specified dimensions designed by Pro/E



By using the finite element method Ansys software, the structural analysis of various

frequency modes is carried out with and without hole in the gas turbine. The output of the

structural analysis at various modes is presented in Figures.3-8.

2.1 Vibration Analysis of Turbine Blade without Hole

Figure 4 Mode 1 frequency – 252.59 Hz

2.2 Vibration Analysis of Turbine Blade with Hole






2.4 Vibration Analysis of Turbine Blade without Hole



Figure 8:Mode 3 frequency – 841.4 Hz

3. TEMPERATURE ANALYSIS USING ANSYS

Figure 9 illustrates the temperature distribution analysis of turbine blade.

Figure 9 Temperature distribution analysis of turbine blade



4. COMPUTATIONAL FLUID ANALYSIS USING ANSYS FLUENT

Fluent uses the finite-volume method to solve the governing equations for a fluid. It provides

the capability for Computational Fluid Dynamics (CFD) to simulate fluid flow problems. In

this problem, Fluent is used for solving and post-processing. The meshed model of the turbine

blade is obtained as shown in Figure 10 and the boundary conditions employed for gas turbine

blade is shown in Figure 11.

Figure 10 Meshed model of gas turbine blade

Figure 11 Boundary conditions for gas turbine blade

5. CFD ANALYSIS RESULTS

The results of CFD analysis carried out such as pressure and temperature distribution at

different parameters are presented in Figures 12-18.

CASE: I

Figure 12 Pressure distribution (Pa), V = 204 m/s, T = 1100 K & M = 0.6



Figure 13 Temperature Distribution (K), T = 1100 K & M = 0.6

CASE: II

Figure 14 Pressure Distribution (Pa),V = 272 m/s,T =1100 K & M = 0.8

Figure 15 Temperature Distribution (K),T = 1100 K & M = 0.8

CASE: III

Figure 16 Pressure distribution (Pa), V = 340 m/s, T = 1100 K, M = 1



Figure 17 Temperature distribution (K), T = 1100 K, M = 1

Figure 18 Solution convergence

Table 2 presents the comparison between the result of the vibration structural analysis of

the gas turbine with hole and without hole.

Table 2: Comparison of gas turbine vibration analysis

Turbine Blade Without HoleTurbine Blade With Hole

MODE 1 252.59 Hz MODE 1 254.43 Hz

MODE 2 450.63 Hz MODE 2 452.54 Hz

MODE 3 836.11 Hz MODE 3 841.40 Hz

6. CONCLUSIONS

In this work, the FEA modelling, structural analysis and CFD Fluent analysis of high speed

gas turbine blades are presented. The schematic diagrams of turbine blade are drafted by using

pro/E wild fire 4.0 version as per the standard dimension. The following key points are

observed during the analysis.

1. The vibration analysis of the turbine blade with hole and without hole is carried out by

using ANSYS v12 software. From the result of analysis induced vibration in both

blades are same. So mechanically satisfies for the blade.

2. The CFD ANSYS package is used for temperature variation of the turbine blade. From

the result of analysis it was found that the reducing temperature of the turbine blade at

the range of 236 K. It indicates that the turbine blades are effectively cooling. While

effective cooling of the turbine blades can increase their life span, it can also reduce

the thermal efficiency of the engine.



REFERENCES

[1] T. Sadowski, P. Golewski, Multidisciplinary analysis of the operational temperature

increase of turbine blades in combustion engines by application of the ceramic thermal

barrier coatings (TBC) Computational Materials Science, Elsevier, Vol 50, Issue 4, Pp

1326-1335, Feb 2011.

[2] Kyung Min Kim, Jun Su Park, Dong Hyun Lee, Woon Lee, Analysis of conjugated heat

transfer, stress and failure in a gas turbine blade with circular cooling passages,

Engineering Failure Analysis, Elsevier, Vol 18, Issue 4, Pp 1212-1222, Jun 2011.

[3] Heeyoon Chung, Jun Su Park, Ho-SeongSohn, Dong- Ho Rhee, Trailing edge cooling of a

gas turbine blade with perforated blockages with inclined holes, International Journal of

Heat and Mass Transfer, Elsevier, Vol 73, Pp 9-20, Jun 2014.

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Documents

MODELLING, STRUCTURAL ANALYSIS AND CFD FLUENT ANALYSIS OF HIGH SPEED GAS TURBINE · PDF file · 2017-09-25CFD FLUENT ANALYSIS OF HIGH SPEED GAS TURBINE BLADES ... Gas turbine blades,