Volume 30 Issue 4
Apr.  2015
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Article Navigation >  Journal of Aerospace Power  > 2015  >  30(4): 891-900
CHEN Zhong-liang, JIANG Bin, ZHENG Qun, ZHANG Xiao-long, TAN Chun-lai. Optimized profile of high subsonic axial flow compressor[J]. Journal of Aerospace Power, 2015, 30(4): 891-900. doi: 10.13224/j.cnki.jasp.2015.04.016
Citation: CHEN Zhong-liang, JIANG Bin, ZHENG Qun, ZHANG Xiao-long, TAN Chun-lai. Optimized profile of high subsonic axial flow compressor[J]. Journal of Aerospace Power, 2015, 30(4): 891-900. doi: 10.13224/j.cnki.jasp.2015.04.016
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Optimized profile of high subsonic axial flow compressor

doi: 10.13224/j.cnki.jasp.2015.04.016

  • College of Power and Energy Engineering, Harbin Engineering University, Harbin 150001, China

  • Received Date: 2013-11-15
  • Publish Date: 2015-04-28
    Abstract
  • An optimization design method of compressor profile was studied by combining computational fluid dynamics and numerical optimization algorithm. The profile of a high subsonic axial flow compressor was taken as the research object with inlet Mach number of 0.7. The optimization variables were selected by Latin hypercube sampling method and an objective function considering incidence performance was built. Boundary layer transition was also taken into account and the Gamma-Theta transition model was used in numerical simulation. An optimized profile of high subsonic axial flow compressor that can improve incidence performance and reduce total pressure loss was obtained. The results show that the optimized profile can significantly reduce total pressure loss at both incidences of -4 degree and +4 degree with inlet Mach number from 0.2 to 0.8. It can increase the incidence of lower pressure loss by more than 4 degree at the design point (inlet Mach number of 0.7). In addition, the optimized profile can reduce the optimum consistency by 20% and improve the flow characteristics of cascade at low Reynolds numbers.

     

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