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Medium Scale Jet Engine Design and Design Validation Through Simulation

  • Vamsikrishna Undavalli
  • Anmol Kumar
  • Yash Gupta
  • S. Ramanan
  • Md. Saquib Reza
Conference paper
Part of the Lecture Notes in Mechanical Engineering book series (LNME)

Abstract

This paper investigates the development of preliminary design methodology for the core components of medium scale jet engine viz. Diffuser, compressor, combustion chamber, turbine and nozzle and the validation of the conceptual design. The preliminary design process begins with aerodynamic analysis and its reliance on empirical relations, limiting the dimensional constraints and performance demands. The engine has been designed to operate with mass flow rate of 1 kg/s, compression ratio 6, on fuel methane having a calorific value of 42,800 kJ/K, with turbine inlet temperature of 1800 K which drives the compressor at 17,000–22,000 RPM and nozzle which generates thrust mass flow rates greater than 500 N. An overall pressure ratio of 0.75 is selected to make the engine self-sustainable at operating regimes with the overall efficiency of about 38%. The parametric results were compared with simulated results using different approaches to optimize the component design by adopting different techniques and validation of the design.

Keywords

Medium scale jet engines Compression ratio Overall efficiency Overall pressure ratio Self-sustainable Turbine inlet temperature 

Nomenclature

A

Area

T

Temperature

P

Pressure

TIT

Turbine Inlet Temperature

\( \dot{m} \)

Mass flow rate

M

Mach number

ρ

Density

V

Velocity

η

Efficiency

c

Specific heat

γ

Specific heat ratio

π

Pressure ratio

τ

Temperature ratio

Subscripts

abs

Absolute

Tan

Tangential

rad

Radial

o

Stagnation

ov

Overall

p

Propulsive

t

Thermal

C

Cold Section

H

Hot Section

1

Diffuser Inlet

2

Compressor Inlet

3

Combustion Chamber Inlet

4

Turbine Inlet

5

Nozzle Inlet

6

Nozzle Exit

V1

Absolute stage exit velocity

U1

Tangential stage exit velocity

α

Gas angles

 αin

Absolute inlet gas angles

αexit

Absolute exit gas angles

α1

Absolute Inlet gas angle

α2

Absolute outlet gas angle

cx

Stator chord

cr

Rotor chord

s

Spacing

Zs

Tangential force coefficient of stator

ϒ

Blade angle

ϒ1

Inlet blade angle

ϒ2

Outlet blade angle

Λ

Stagger angle

б

Solidity

D

D + hx

d

Disc diameter

hx

Blade position above disc

Cl

Lift coefficient for rotor

Notes

Acknowledgements

Asst. Prof. Ankur Vats, Asst. Prof Jayanth Sinha and Dr. Konark Arora for their valuable guidance

References

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Copyright information

© Springer Nature Singapore Pte Ltd. 2018

Authors and Affiliations

  • Vamsikrishna Undavalli
    • 1
  • Anmol Kumar
    • 1
  • Yash Gupta
    • 1
  • S. Ramanan
    • 1
  • Md. Saquib Reza
    • 1
  1. 1.Amity Institute of Aerospace Engineering, Amity UniversityNoidaIndia

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