In order to deeply analyze the application prospect of the boundary layer suction technique on the compressor, the flow control effect of endwall suction scheme on the tip leakage flow of a compressor cascade at a large incidence angle with complex internal flow structure and different loss proportion from the case at design incidence angle, was studied numerically, as well as on the overall aerodynamic performance. The results show that the suction scheme directly affects the structure of the tip leakage flow and makes the onset position of the tip leakage vortex move backward, which weakens the intensity and influence range of the tip leakage flow, thus improving the cascade performance in the tip region. At the large incidence angle, large flow suction makes the boundary layer separation in the low span area advance, and the corner separation region at the gap-free end expands to the upper. The position of the separation vortex shedding rises from 10% blade span under the condition without suction to about 70% blade span under the condition with the suction flow rate of 0.7%, and the separation loss increases. The overall performance of the cascade at the large incidence angle mainly depends on the increase of separation loss, while the effect of the decrease of leakage loss on it is greatly reduced. With suction, the total pressure loss coefficient of the cascade increases by about 5.7% at the incidence angle of +8°.

为了深入分析边界层抽吸技术在压缩机上的应用前景，端壁抽吸方案对大入射角，内部流结构复杂，损失比例不同的压缩机叶栅叶尖泄漏流的流量控制效果。对设计入射角的壳体进行了数值研究，并对整体空气动力学性能进行了研究。结果表明，吸气方式直接影响尖端泄漏流的结构，使尖端泄漏涡的起始位置向后移动，削弱了尖端泄漏流的强度和影响范围，从而改善了尖端的级联性能。地区。在大入射角处，大的吸力使低跨度区域中的边界层分离提前，无间隙端的角部分离区域向上方扩展。分离涡旋脱落的位置从无抽吸条件下的叶片跨度的10％上升到抽吸流量为0.7％的条件下的叶片跨度的约70％，分离损失增大。级联在大入射角时的整体性能主要取决于分离损失的增加，而泄漏损失减少对其的影响则大大降低。在吸力作用下，入射角为+ 8°时，叶栅的总压力损失系数增加了约5.7％。并且分离损失增加。级联在大入射角时的整体性能主要取决于分离损失的增加，而泄漏损失减少对其的影响则大大降低。在吸力作用下，入射角为+ 8°时，叶栅的总压力损失系数增加了约5.7％。并且分离损失增加。级联在大入射角时的整体性能主要取决于分离损失的增加，而泄漏损失减少对其的影响则大大降低。在吸力作用下，入射角为+ 8°时，叶栅的总压力损失系数增加了约5.7％。