Aerodynamic Design of a single stage Axial Flow Compressor using CFD approach

Authors

  • Kiran D Chaudhari  Department of Mechanical Engineering, Prof. Ram Meghe Institute of Technology & Research, Badnera, Amravati, Maharashtra, India
  • Prof. Dr. N. A. Wankhede  Department of Mechanical Engineering, Prof. Ram Meghe Institute of Technology & Research, Badnera, Amravati, Maharashtra, India

Keywords:

Axial flow compressor, aerodynamic design, CFD modeling, Blade design and profiling, optimized performance.

Abstract

The performance of axial flow compressor has major impact on overall performance of gas turbine engine. The paper deals with numerical analysis of a single stage, subsonic axial flow compressor using commercial CFD code of AxSTREAM. The aerodynamic design and blade profiling has been carried out using CFD software. The research starts with design of the high pressure ratio compressor blade sections which yield a single stage pressure rise up to 1.21, the constant tip diameter of the compressor rotor blade for 15.5 kg/s, 14800 RPM, 276.5 KW power with a tip speed 167.7 m/s. Further the design is optimized for minimum total pressure loss. Analytical results compared with the numerical analysis.

References

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International Journal of Scientific Research in Science, Engineering and Technology

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Published

2018-03-30

Issue

Volume 4, Issue 4, March-April-2018

Section

Research Articles

License

Copyright (c) IJSRSET

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This work is licensed under a Creative Commons Attribution 4.0 International License.

How to Cite

[1]
Kiran D Chaudhari, Prof. Dr. N. A. Wankhede, " Aerodynamic Design of a single stage Axial Flow Compressor using CFD approach, International Journal of Scientific Research in Science, Engineering and Technology(IJSRSET), Print ISSN : 2395-1990, Online ISSN : 2394-4099, Volume 4, Issue 4, pp.132-140, March-April-2018.