附面层吸除对大转角压气机叶栅气动性能影响的数值研究
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V232

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国家自然科学基金资助(50236020)


Numerical Investigation of Boundary Layer Suction in Compressor Cascade with Large Turning Angles
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    摘要:

    数值模拟了低速条件下附面层吸除对某大转角压气机叶栅气动性能的影响。结果表明,叶栅进口马赫数一定时,小吸气量下存在使叶栅总压损失降低最大的最佳吸气位置,大吸气量时吸气位置对损失影响减弱;随吸气量增加,吸力面角区低能流体积聚明显减小,气流折转能力加强,叶栅负荷增加,总压损失降低最高达28.2%;吸气导致的栅内扩压能力恢复和通道涡三维分离效应是确定最佳吸气位置及吸气量的判定原则。

    Abstract:

    Numerical study of the effects of suction location and suction flow rate on performance of low-speed compressor cascade with large turning angles shows that with the same inlet Mach number,the optimal suction location,corresponding to the least cascade total loss,exists at a lower suction flow rate,and the decrease of total loss is not sensitive to the suction location at a higher level of suction flow rate.As suction flow rate increases,the accumulation of low energy fluid in the suction corner is alleviated,and the flow turning as well as the cascade load increases,therefore,total loss is reduced by 28.2% at most.The diffusion recovery due to the boundary layer suction and the separation of passage vortex are two main factors for the selection of the optimal suction location and suction flow rate.

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宋彦萍,陈浮,赵桂杰,陈开莹,王仲奇.附面层吸除对大转角压气机叶栅气动性能影响的数值研究[J].航空动力学报,2005,20(4):561~566. SONG Yan-ping, CHEN Fu, ZHAO Gui-jie, CHEN Kai-Ying, WANG Zhong-qi. Numerical Investigation of Boundary Layer Suction in Compressor Cascade with Large Turning Angles[J]. Journal Of Aerospace Power,2005,20(4):561-566.

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  • 收稿日期:2004-06-03
  • 最后修改日期:2004-09-15
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