Volume 34 Issue 5
May  2019
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Numerical simulation on flat baffle inlet distortion of axial compressor[J]. Journal of Aerospace Power, 2019, 34(5): 1153-1165. doi: 10.13224/j.cnki.jasp.2019.05.022
Citation: Numerical simulation on flat baffle inlet distortion of axial compressor[J]. Journal of Aerospace Power, 2019, 34(5): 1153-1165. doi: 10.13224/j.cnki.jasp.2019.05.022

Numerical simulation on flat baffle inlet distortion of axial compressor

doi: 10.13224/j.cnki.jasp.2019.05.022
  • Received Date: 2018-10-07
  • Publish Date: 2019-05-28
  • The coupling numerical simulation of the low-speed, high-subsonic, transonic axial compressor with the flat-baffle-type distortion generator was carried out respectively. The flow field characteristics of compressor under the flat-baffle-type distortion condition and the stall boundary of the different types of compressors were analyzed. It was found that the circumferential flow in the inlet plane of the low-speed compressor, the influence of the flat baffle angular vortex on the high subsonic compressor tip leakage’s flow path, and the change of passage shock wave’s intensity and location in the transonic compressor rotor passage were important factors of distortion flow to the stability boundary of different types of compressor respectively.

     

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