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

Authors(2) :-Kiran D Chaudhari, Prof. Dr. N. A. Wankhede

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.

Authors and Affiliations

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

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

  1. A. J. Wennerstorm: "Experimental study of a high through flow transonic axial compressor stage", ASME vol.106, July 1984.
  2. S. J. Galllimore "Axial Flow Compressor design" Journal of Mechanical Engineering Science, in 1999.
  3. Leonid Moroz, Yuri Govorushchenko, Petr Pagur "A Uniform Approach To Conceptual Design Of Axial Turbine / Compressor Flow Path" The Future of Gas Turbine Technology, October 2006
  4. Q. H. Nagpurwala, S.A.Guruprasad, H. Girigoswamy, B. R. Pai. "Experimental and Analytical studies of a transonic stator having CDA sections with end bends" Propulsion Div. NAL Bengalore, ISABE 95-7074
  5. Ernesto Benin "Three-Dimensional Multi-Objective Design Optimization of a Transonic Compressor Rotor" Published in Journal of Propulsion and Power, May 2004
  6. Sang-Yun LeeKwang-Yong Kim, "Design optimization of axial flow compressor blades with three-dimensional Navier-Stokes solver", KSME International Journal, September 2000, Volume 14, Issue 9, pp 1005-1012
  7. Dr. S. A. Channiwala, Nilesh P. Salunke, "Design and Analysis of a Controlled Diffusion Aerofoil Section for an Axial Compressor Stator and Effect of Incidence Angle and Mach No. on Performance of CDA" International Journal of Fluid Mechanical and System, Jan 2010
  8. K. Pandey, K M?; Chakraborty, S?; Deb, "CFD analysis of flow through compressor cascade", International Journal of Soft Computing and Engineering (IJSCE) ISSN: 2231-2307, Volume-2, Issue-1, March 2012
  9. Dr. S. A. Channiwala, Nilesh P. Salunke, "Literature Review On Aerodynamic Design Of Axial Flow Compressor", January 2011, first international conference on sunrise technologies, i-COST 2011
  10. Chan-Sol Ahn and Kwang-Yong Kim, "Aerodynamic Design Optimization of an Axial Flow Compressor Rotor", ASME Turbo Expo 2002: Power for Land, Sea, and Air, Volume 5: Turbo Expo 2002, Parts A and B, ISBN: 0-7918-3610-X, June 3-6, 2002
  11. Horlock, J. H., "Axial Flow Compressors" Butteworth 1958.
  12. Ronald H. Aungier "Axial-Flow Compressors: A Strategy for Aerodynamic Design and Analysis" ASME Press

Publication Details

Published in : Volume 4 | Issue 4 | March-April 2018
Date of Publication : 2018-03-30
License:  This work is licensed under a Creative Commons Attribution 4.0 International License.
Page(s) : 132-140
Manuscript Number : IJSRSET1841322
Publisher : Technoscience Academy

Print ISSN : 2395-1990, Online ISSN : 2394-4099

Cite This Article :

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.
Journal URL : http://ijsrset.com/IJSRSET1841322

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