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Proceedings of the International Conference on Modern Research in Aerospace Engineering pp 21–33Cite as

Medium Scale Jet Engine Design and Design Validation Through Simulation

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Part of the book series: Lecture Notes in Mechanical Engineering ((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.

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Abbreviations

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

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

References

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Acknowledgements

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

Author information

Authors and Affiliations

  1. Amity Institute of Aerospace Engineering, Amity University, Noida, 201303, Uttar Pradesh, India

    Vamsikrishna Undavalli, Anmol Kumar, Yash Gupta, S. Ramanan & Md. Saquib Reza

Authors
  1. Vamsikrishna Undavalli
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  2. Anmol Kumar
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  3. Yash Gupta
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  4. S. Ramanan
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  5. Md. Saquib Reza
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Corresponding author

Correspondence to Md. Saquib Reza .

Editor information

Editors and Affiliations

  1. Amity Institute of Aerospace Engineering, Amity University, Noida, Uttar Pradesh, India

    Sanjay Singh

  2. DTC Secretariat, Ghaziabad, Uttar Pradesh, India

    Pushkar Raj

  3. Department of Aerospace Engineering and Engineering Mechanics, College of Engineering and Applied Sciences, University of Cincinnati, Cincinnati, Ohio, USA

    Samir Tambe

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© 2018 Springer Nature Singapore Pte Ltd.

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Cite this paper

Undavalli, V., Kumar, A., Gupta, Y., Ramanan, S., Reza, M.S. (2018). Medium Scale Jet Engine Design and Design Validation Through Simulation. In: Singh, S., Raj, P., Tambe, S. (eds) Proceedings of the International Conference on Modern Research in Aerospace Engineering. Lecture Notes in Mechanical Engineering. Springer, Singapore. https://doi.org/10.1007/978-981-10-5849-3_3

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  • DOI: https://doi.org/10.1007/978-981-10-5849-3_3

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  • Publisher Name: Springer, Singapore

  • Print ISBN: 978-981-10-5848-6

  • Online ISBN: 978-981-10-5849-3

  • eBook Packages: EngineeringEngineering (R0)

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