Volume 28 Issue 11
Nov.  2013
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Article Navigation >  Journal of Aerospace Power  > 2013  >  28(11): 2483-2494
SHA Xin-guo, YAN Ming, LIU Zheng-liang. Numerical simulation of inter-stage bleeding in highly-loaded multistage axial compressor[J]. Journal of Aerospace Power, 2013, 28(11): 2483-2494.
Citation: SHA Xin-guo, YAN Ming, LIU Zheng-liang. Numerical simulation of inter-stage bleeding in highly-loaded multistage axial compressor[J]. Journal of Aerospace Power, 2013, 28(11): 2483-2494.
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Numerical simulation of inter-stage bleeding in highly-loaded multistage axial compressor

  • 1.

    National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

  • 2.

    China Academy of Aerospace Aerodynamics, China Aerospace Science and Technology Corporation, Beijing 100074, China

  • Received Date: 2012-10-30
  • Publish Date: 2013-11-28
    Abstract
  • Taking a highly-loaded eight-stage axial compressor as an object of research, the effect of inter-stage bleeding on compressor performance, inner flow-field and inter-stage matching in highly-loaded multistage axial compressor was investigated numerically. The result shows that inter-stage bleeding can significantly improve the compressor's performance. The bleeding results in 1% increase of the inlet mass flow and of 1.5% increase of the highest efficiency. In addition, the bleeding can decrease the pressure and density of air near the bleeding pores. This leads to an increase of mass flow upstream with the largest load position of rotors moving to downstream as well as a decrease of the mass flow downstream with the largest load position of rotors kept steady proximately. Moreover, bleeding contributes to change the working point position of stages in upstream and downstream of the bleeding position and alter the inter-stage matching of compressor. At the same time, bleeding at the trailing edge of stator could diminish thickness of boundary layer and change inlet condition of rotor downstream.

     

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