Abstract: Experimental investigation was carried out to study the effects of the boundary layer suction implemented close to the suction surface on the endwall on improving the aerodynamic performance of a compressor cascade with a large camber angle. The flow fields of the cascade and the static pressure by tapping on the cascade surfaces were measured, and the ink-trace flow visualization was also conducted. Experimental results show that the applied manner of boundary layer suction mainly affects the suction and endwall corner region and the load of the blade root redistribution after suction. Suction before the separation in endwall corner region happening delays the flow separation, decreases cascade losses, and improves the flow condition of the endwall region effectively. But suction after the separation has occurred even worsens the flow field and enhances the blending of the low energy fluid, and increases losses.

Key words: Endwall boundary layer suction⁺; Suction position⁺; High-turning diffusion cascade; Experimental investigation

摘要： 实验研究了低速条件下在端壁近吸力面处进行附面层吸除对某大转角扩压叶栅性能的影响。对叶栅出口截面参数和叶片型面静压进行了测量,并在叶片表面及端壁进行了墨迹流动显示。结果表明,端壁抽吸主要影响了吸力面/端壁角区,重新分配叶片根部负荷。在角区未发生分离的位置开始抽吸可有效推迟叶栅内的角区分离,降低损失,改善叶栅端区流动；而在角区已经发生分离的弦向位置开槽吸气则引起了局部回流,恶化了流场,增加了低能流体的掺混和气动损失。

关键词: 端壁吸气⁺;吸气位置⁺;大转角扩压叶栅;实验研究