Volume 27 Issue 2
Feb.  2012
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XIE Fang, CHU Wu-li, ZHANG Hao-guang. Influence of shock waves/leakage vortex/boundary layer separation interaction in a single-stage transonic axial compressor[J]. Journal of Aerospace Power, 2012, 27(2): 425-430.
Citation: XIE Fang, CHU Wu-li, ZHANG Hao-guang. Influence of shock waves/leakage vortex/boundary layer separation interaction in a single-stage transonic axial compressor[J]. Journal of Aerospace Power, 2012, 27(2): 425-430.

Influence of shock waves/leakage vortex/boundary layer separation interaction in a single-stage transonic axial compressor

  • Received Date: 2011-05-09
  • Rev Recd Date: 2011-08-02
  • Publish Date: 2012-02-28
  • Three-dimensional(3-D) numerical simulations were conducted to analyze the flow field in transonic rotors Rotar 37. The results with design tip clearance were compared with no tip clearance condition. Mutual influence of shock, boundary layer separation, clearance leakage the vortex accelerated the occurrence of stalled. Reduce clearance can enlarge the steady border. The suction position applied on passive control technology to improve port flow condition was given.

     

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