Volume 21 Issue 2
Apr.  2006
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FENG Guo-tai, ZHANG Yong-jun, CHEN Fu, SU Jie-xian. Influence of Inlet Boundary Layer on Flow Field Performance of the 2D Compressor Bowed Stator Vane[J]. Journal of Aerospace Power, 2006, 21(2): 254-260.
Citation: FENG Guo-tai, ZHANG Yong-jun, CHEN Fu, SU Jie-xian. Influence of Inlet Boundary Layer on Flow Field Performance of the 2D Compressor Bowed Stator Vane[J]. Journal of Aerospace Power, 2006, 21(2): 254-260.

Influence of Inlet Boundary Layer on Flow Field Performance of the 2D Compressor Bowed Stator Vane

  • Received Date: 2005-09-15
  • Rev Recd Date: 2006-02-10
  • Publish Date: 2006-04-28
  • For several given types of inlet boundary layer,a numerical investigation on flow field of bowed stator vanes under two inlet subsonic Mach numbers was carried out.It was found that the ability of improving diffusion cascade performance was affected by some characteristics of the inlet boundary layer.The characteristics included two aspects:inlet boundary layer thickness and inlet boundary layer momentum loss thickness.When boundary layer is thicker or momentum loss thickness was greater,the flow capacity is evidently increased near end-wall under Mach number 0.2.Consequently,the cascade performance is improved and total pressure loss is reduced near suction corner to a greater extent.Under Mach number 0.7,though the increase of mass flow density is less,because of the high end-wall loss,improvement of end-wall performance will bring more profits to the overall cascade performance.

     

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