DESIGN AND ANALYSIS OF ROCKET NOZZLE

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DESIGN AND ANALYSIS OF ROCKET NOZZLE

Sangati Hasseni*1, N Francis*2, M Ravi Sankara Varaprasad*3,

K Nagaraju*4, G Md Javeed Basha*5 *1PG Student, ME Department, St.Johns College Of Engineering & Technology, Yemmiganur, India.

*2,3,4,5Assistant Professor, ME Department, St.Johns College Of Engineering & Technology,

Yemmiganur, India.

ABSTRACT

The nozzle is used to transform the chemical thermal electricity generated withinside the combustion chamber

into kinetic electricity. The nozzle converts the low speed, excessive stress, excessive temperature fueloline

withinside the combustion chamber into excessive speed fueloline of decrease stress and temperature. Nozzle

is a tool designed to manipulate the price of waft, speed, path, mass, shape, and/or the stress of the flow that

exhaust from them. Nozzles are available in quite a few sizes and styles relying at the assignment of the rocket,

that is very vital for the know-how of the overall performance traits of rocket. Convergent divergent nozzle is

the maximum generally used nozzle seeing that in the usage of it the propellant may be heated in combustion

chamber. In this thesis evaluation is finished to the convergent divergent nozzle via way of means of converting

extraordinary nozzle diameters and extraordinary fluids at extraordinary velocities. We modeled convergent

divergent nozzle converting with extraordinary nozzle diameters and Analyzed the convergent divergent

nozzle with extraordinary mass waft charges to decide the stress drop, warmness switch coefficient, speed,

mass waft price and warmth switch price for the fluid via way of means of CFD method.

Keywords: Nozzle, Fueloline, Rocket, Coefficient, CFD.

I. INTRODUCTION

Advancements in the era of Diesel Injection (DI) structures have contend in important function in the upgrades

which can be created as much as the cutting-edge motive. Combining the discount in nozzle passage diameters

thru elevated waft traits with inflated injection pressures offers a risk to broaden engines that consists of

excessive energy density and decreased emissions. The first drawback to the ones elegant spray hollow

geometries is they generally go through a reduction of energy output during long term operation. Alternative

research have regarded those vital formations of deposits due to the fact the principle motive for this conduct.

Basic mechanisms are frequently wont to make a case for the formation and elimination of deposits in burning

engines These mechanisms act severally of the scenario of formed deposits (e.g. injection nozzles, warmness

changer) and of the combustion approach (e.g. IDI, DI; diesel or gasoline). The version delineate in the observe

illustrates the interplay of a wall with the advent waft regime. The shipping of debris to the wall relies at the

approach of thermophores is this system finally ends up withinside the pressure of fueloline debris in the path

of the temperature depression. It is simplified with partner diploma growing temperature differential among

wall (bloodless) and fluid (warm). This approach outcomes is partner diploma growing awareness of deposit-

constructing debris near the wall. High a couple of turbulence near the wall may want to cut back the pressure

of the aerosol another time to a norm, compensating for partner diploma inflated temperature difference. The

deposits place unit composed of linked debris (stable and liquid) and fueloline. Condensation and floor

assimilation of vaporous compounds on the bloodless wall promotes the formation approach. At this time, the

growth of the deposits is presently mainly stimulated via way of means of the sticking out, impaction and

incorporation of debris The floor assimilation of vaporous factors and consequently the chemical reactions (as

shift, dehydration and chemical change, etc.), bring about the compaction of the deposits. The elimination of

deposits has analogous bodily mechanisms. The mechanism is response destroying the natural compounds in

the coating Evaporation and motion cut back the vaporous fraction dissolved in the deposits. Abrasion is

resulting from strong mechanics forces and breaking-off, as a consequence of warm temperature modifications,

main to heterogeneous extensions of the wall and deposit layer. The corresponding reducing off stresses

provoke the breaking-off approach The soluble fraction of the deposits is washed off via way of means of

solvents (e.g. water as solvent for salt compounds)





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II. LITERATURE SURVEY

Design and Optimization of Fuel Injection System in Rocket Using Biodiesel – A Review H. M. Pate Fuel injection

is structures for presenting excessive pressurize gasoline to most blending of gasoline with air in an inner

combustion engine. Direct Injection (DI) Systems as utilized in DI engines, wherein the gasoline is injected

immediately right into a combustion chamber shaped withinside the cylinder itself. The gasoline injector

immediately injects gasoline into the direct gasoline injection device. The injector is a completely complex

component, and big studies has been finished to enhance it.In my paintings indicating the improvement of

gasoline injector device to lessen chocking hassle that's normally take place in bio diesel engine. The injection

nozzles and their respective nozzle holders are vitally vital additives located among the in-line injection pump

and the diesel engine, its capabilities are as metering the injection of gasoline, control of the gasoline, defining

the price-of-discharge curve, Sealing-off in opposition to the combustion, chamber. Mechanical kind injectors

utilized in direct injection device. When biodiesel is used withinside the rocket choking hassle is created in

gasoline injector. Therefore, we optimize the layout of gasoline injector component, and attempted to save you

the chocking hassle. The diesel gasoline injector device immediately injects gasoline into the device with out

chocking.

M. Volmajer et al [4] had numerical and experimental outcomes of the nozzle gasoline waft evaluation for a 4-

hollow injection nozzle Bosch DLLA 148 S 311376 are supplied. The gasoline waft coefficients acquired from

the experimental outcomes at consistent waft situations withinside the nozzle are as in comparison with the

outcomes of the CFD evaluation. The gasoline waft coefficients acquired from the experimental outcomes at

consistent waft situations withinside the nozzle are as in comparison with the outcomes of the CFD evaluation.

From the supplied outcomes the subsequent conclusions might be made. Flow coefficient trying out tool built

on the ERL yields sufficiently precision, with affordable uncertainties of the dimension. To refine the precision

of the dimension, via way of means of defining the precise fee of the stress difference, the stress downstream of

the nozzle need to be measured, or the nozzle function need to be modified so, that the fluid could be injected

immediately into the measuring Plexiglas. For the identical motive, Plexiglas cylinder with excessive ovalness

need to get replaced with the glasslPlexiglas cylinder with right circle cross-phase. The supplied trying out tool

additionally allows the dimension of the waft coefficient one at a time for every nozzle hollow, which brings

higher assessment with the outcomes of CFD evaluation whilst the simplified fashions, introducing most

effective one hollow, are carried out. Zhijun Li et al had investigates the outcomes of producing versions in

gasoline injectors at the engine overall performance with emphasis on emissions. The versions are considered

inside a Reliability-Based Design Optimization (RBDO) framework. A decreased model of Multi-Zone Rocket

Simulation (MZDS), MZDS-lite, is used to allow the optimization observe. The numerical noise of MZDS-lite

prohibits using gradient-primarily based totally optimization methods. Therefore, surrogate fashions are

evolved to clear out the noise and to lessen computational cost.

III. MODELING AND ANALYSIS

3D MODEL OF DIESEL NOZZLE

Figure: Nozzle 3D model with dia 50mm





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ANALYSIS USING ANSYS

→→Ansys → workbench→ select analysis system → fluid flow fluent → double click

→→Select geometry → right click →new geometry

Figure: 1 solid model of nozzle imported in CFD

→→ Select mesh on work bench → right click →edit → select mesh on left side part tree → right click → generate

mesh →





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MESHED MODEL

Figure: Meshed model of nozzle in CFD

SPECIFYING THE BOUNDARIES FOR INLET & OUTLET

Figure: Nozzle model with specified inlet and outlet conditions

4.4 THERMAL ANALYSIS OF NOZZLE

Material –brass

Figure: Imported model of rocket nozzle made of brass





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Meshed model

Figure: Meshed model of rocket nozzle made of brass

Temperature

Figure: Temperature variation in the nozzle





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Heat flux

Figure: 2Heat flux analysis of nozzle

Material –aluminum alloy

Temperature

Figure: Temperature variation in the nozzle





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Heat flux

Figure: Heat flux analysis in a rocket nozzle

IV. RESULTS AND DISCUSSION

Table: Result for various parameters for different inlet velocities and nozzle diameters

Nozzle

dia.

Inlet

velocity

(m/s)

Pressure

(Pa)

Velocity

(m/s)

Heat

transfer

coefficient

(w/m2-k)

Mass flow

rate (kg/s)

Heat transfer

(W)

50

200 1.25e+10 2.98e+03 3.59e+05 1.138945 11540.5

300 6.96e+09 4.46e+03 5.10e+05 2.289245 29275

400 3.12e+09 5.99e+03 6.56e+05 3.087343 31294

40

200 1.83e+10 3.58e+03 3.76e+05 1.0457764 10600

300 1.03e+10 5.38e+03 5.30e+05 2.192199 22219

400 4.53e+09 7.17e+03 6.80e+05 2.9847107 30249

30

200 4.18e+10 5.36e+03 6.90e+05 0.16120148 1634.3125

300 2.34e+10 8.05e+03 8.05e+05 0.44642 4520.625

400 1.04e+10 1.07e+04 1.25e+06 0.8333587 8450.75

GRAPHS:

Various parameters like pressure, velocity, heat transfer coefficient, heat transfer and mass flow rate are

compared for three nozzle diameters 50mm, 40mm, 30mm and the report is concluded.





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Figure: Comparison of pressure for different nozzle diameter and different inlet velocities

Figure: Comparison of velocity for different nozzle diameter and different inlet velocities

0

10

20

30

40

50

60

70

80

200 300 400

pre

ssu

re(P

a)*

10ᴧ9

inlet velocities(m/s)

30mm dia

40mm dia

50mm dia

0

5

10

15

20

25

30

200 300 400

vel

oci

ty(m

/s)*

10ᴧ3


30mm dia

40mm dia

50mm dia





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Figure: Comparison of heat transfer coefficient for different nozzle diameter and different inlet velocities

Figure: Comparison of heat transfer for different nozzle diameter and different inlet velocities

0

5

10

15

20

25

30

200 300 400

Hea

t tr

an

sfer

coef

fici

ent

(w/m

2-k

)


30mm dia

40mm dia

50mm dia

0

1

2

3

4

5

6

7

8

200 300 400

hea

t tr

an

sfer

(W)


30mm dia

40mm dia

50mm dia





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Figure: Comparison of mass flow rate for different nozzle diameter and different inlet velocities

Table: Thermal analysis result table

Material Temperature (K) Heat flux(W/mm2)

Min Max

Brass 320.02 350 0.76451

Aluminum 323.59 350 0.87036

V. CONCLUSION

Nozzles come in a variety of shapes and sizes depending on the mission of the rocket, this is very important for

the understanding of the performance characteristics of rocket. Convergent divergent nozzle is the most

commonly used nozzle since in using it the propellant can be heated in combustion chamber. In this thesis the

analysis is done on convergent divergent nozzle by changing different nozzle diameters and different velocities.

Also thermal analysis is done on two materials say brass and aluminum alloy. We modeled convergent

divergent nozzle changing with different nozzle diameters. By observing the CFD analysis of rocket nozzle the

velocity, heat transfer rate and mass flow rate values are increasing with increase in the inlet velocities and

decrease in the nozzle dia. Pressure decreases with increase in inlet velocities and diameter of the nozzle. By

observing the thermal analysis, heat flux is more for aluminum alloy compared with brass material. So it can be

concluded that rocket nozzle efficiency is more when the nozzle diameter decreased and inlet velocity is

increased. n this project we have modeled a suspension frame used in two wheeler. The original cross section

is circular we are changing the model to rectangular cross section. Modeling is done in CREO. It is done

structural and modal analysis on both models of suspension frame using materials Steel and Carbon Epoxy.

Present used material for suspension frame is steel. We are replacing with Carbon Epoxy. The density of Carbon

Epoxy is less than that of Steel, so the weight of the frame reduces when Carbon Epoxy is used. By observing the

results, for both the materials the stress values are less than their respective permissible yield stress values. So

our design is safe. Using rectangular cross section is also safe. By comparing the results for both the cross

sections, the displacement and stress values are less for rectangular cross section than circular cross section. By

comparing the results for steel and carbon epoxy, the stress values are less for carbon epoxy than steel. So it

can conclude that using rectangular cross section and material Carbon Epoxy is better for suspension frame.

0

1

2

3

4

5

6

7

8

200 300 400

Mass

flo

w r

ate

(k

g/s

)


30mm dia

40mm dia

50mm dia





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VI. REFERENCES [1] J.B. Heywood, “Internal Combustion Engine Fundamentals”, McGraw-Hill Book Co, pp 493-494, 1988.

[2] D. Ing. H. Tschöke, “Diesel distributor fuel-injection pumps”, Robert Bosch GmbH, pp 12-53, 1999.

[3] B. Challen R. Baranescu, “Rocket Reference Book” Reed Educational and Professional Publishing Ltd.,

Second Edition, pp.260-301, 1999.

[4] M. Volmajer, B. Kegl, “Experimental and numerical analysis of fuel flow in the rocket injection nozzle",

Journal of Kones. Combustion Engines, Vol. 8, No. 1-2, 2001.

[5] Z. Li, M. Kokkolaras, D. Jung, Panos Y. Papalambros and D. N. Assanis, “An Optimization Study of

Manufacturing Variation Effects on Diesel Injector Design with Emphasis on Emissions”, SAE

International, 2004.

[6] A.J.VonWielligh, “Influence of fuel quality on diesel injector failures”, Fifth International Colloquium

Fuels, Germany, 2005. Property Unit Jatropha oil Jatropha Oil methyl ester Diesel Density at 15°C

kg/m3 918 880 850 Viscosity at 40°C mm2 /s 35.4 4.84 2.60 Flash point °C 186 162 70 International

Journal of Innovations in Engineering and Technology (IJIET) Vol. 2 Issue 1 February 2013 76 ISSN:

2319 – 1058

[7] LI Minghai, CUI Hongjiang, W.Juan, G. Ying, “Improvement of fuel injection system of locomotive diesel

engine”, Journal of Environmental Sciences, pp. S139-S141, 2009.

[8] B. Paul, V. Ganesan, “Flow field development in a direct injection rocket with different manifolds”

International Journal of Engineering, Science and Technology Vol. 2, No. 1, pp. 80-91, 2010.

[9] K. K.Khatri, D. Sharma, S. L. Soni, S. Kumar, D Tanwar, “Investigation of Optimum Fuel Injection Timing

of Direct Injection CI Engine Operated on Preheated Karanj-Diesel Blend” Jordan Journal of Mechanical

and Industrial Engineering Volume 4, pp. 629-640, 2010.

[10] BizhanBefrui, Giovanni Corbinelli, Mario D'Onofrio and Daniel Varble, “GDI Multi-Hole Injector Internal

Flow and Spray Analysis”, SAE International, 2011.

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DESIGN AND ANALYSIS OF ROCKET NOZZLE