实验对比了低速条件下抽吸来流附面层前后某大转角扩压叶栅性能的变化。在叶栅壁面进行了墨迹流动显示,并对叶栅出口截面参数进行了测量。结果表明,入口附面层主要影响的区域是损失比较严重的吸力面/端壁角区。减薄大转角扩压叶栅的入口附面层可有效抑制栅内端壁附近的横向二次流、抑制角区分离、降低损失。当吸气量为入口流量的2.5%时,总压损失降低幅度达24 6%。
Experimental investigation was carried out to study the aerodynamic performance of a high-turning compressor cascade with and without boundary layer suction at the cascade inlet.The ink-trace flow visualization was conducted and the flow fields of the cascade were also measured. Experimental results show that inlet boundary layer mainly influence the suction/endwall corner region,where remarkable losses produced.Boundary layer suction at inlet of the diffusion cascade effectively weakens the cross second flow near the endwall,restrains the corner separation and reduces the losses.When the suction flow rate is 2.5%of the inlet mass flow,total loss is reduced by 24.6% compared with the cascade without inlet boundary layer suction.
参考文献
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