Volume 26 Issue 6
Jun.  2011
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Article Navigation >  Journal of Aerospace Power  > 2011  >  26(6): 1362-1369
WU Ji-chang, LU Xin-gen, ZHU Jun-qiang. Secondary flow analysis for non-axisymmetric endwall on the high-load compressor cascade[J]. Journal of Aerospace Power, 2011, 26(6): 1362-1369.
Citation: WU Ji-chang, LU Xin-gen, ZHU Jun-qiang. Secondary flow analysis for non-axisymmetric endwall on the high-load compressor cascade[J]. Journal of Aerospace Power, 2011, 26(6): 1362-1369.
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Secondary flow analysis for non-axisymmetric endwall on the high-load compressor cascade

  • 1.

    Institute of Engineering Thermophysics, Chinese Academy of Sciences,Beijing 100190,China

  • 2.

    Graduate University of Chinese Academy of Sciences,Beijing 100190,China

  • Received Date: 2010-05-12
  • Rev Recd Date: 2010-07-13
  • Publish Date: 2011-06-28
    Abstract
  • The effectiveness of a non-axisymmetric endwall on a high-load compressor cascade was discussed.First of all,the trigonometric function was used to complete non-axisymmetric endwall profiling.Then the method of calculating the mixed-out secondary loss for the compressor cascade was established.Finally,the detailed numerical simulations were conducted on the cascade flow field with non-axisymmetric hub endwall.Numerical results show that with the non-axisymmetric hub endwall,the loading distribution near the endwall would be changed and the secondary loss would be reduced in both the design and off-design condition.It has been indicated that the mass average total pressure loss can decrease by 9.4% in the design and by 7.7% and 11.8% in the off-design condition(±3°),respectively.When the non-axisymmetric contour height equals to be 4% of blade span,the secondary flow loss should be the lowest.

     

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