Volume 28 Issue 11
Nov.  2013
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WU Pei-gen, WANG Ru-gen, LUO Kai, GUO Fei-fei. Effect of slotted blade on performance of high-turning angle compressor cascades[J]. Journal of Aerospace Power, 2013, 28(11): 2503-2509.
Citation: WU Pei-gen, WANG Ru-gen, LUO Kai, GUO Fei-fei. Effect of slotted blade on performance of high-turning angle compressor cascades[J]. Journal of Aerospace Power, 2013, 28(11): 2503-2509.

Effect of slotted blade on performance of high-turning angle compressor cascades

  • Received Date: 2013-01-25
  • Publish Date: 2013-11-28
  • A practical method to control the separation by cutting a slot through the pressure surface and the suction surface was proposed. A converged turning slot configuration was designed. The flow performance with different incidences was investigated. The experimental result was used to check the CFD result, so as to acquire the quantitative flow field structure. The structural static analysis was made. The results show that, in the incidence of 4 degree, the application of slot decreases the wake width of cascades by 16.7%, and decreases the peak of total pressure loss coefficient by 6.07%. In the incidence of 6 degree, the application of slot decreases the peak of total pressure loss coefficient by 14.7%. Fluid can flow from the pressure side to the suction side with slot configuration. The injection air increases the velocity of boundary layer, therefore enhancing its ability to resist the flow separation. Consequently it can decrease the total pressure loss, increase the static pressure ratio, and expand the stability range. It is thus necessary to reduce the stress concentration on fore wall of channel.

     

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