Abstract: This paper presents results of experimental investigations carried out to explore the effects of endwall boundary layer suction on principal vortices and the performance of high-turning compressor cascades. Section measurements were conducted at ten different axial positions distributed from upstream to downstream of the rectangular cascade. The inlet Mach number is about 0.23. Experimental results demonstrate that the evolution of majority vortices in the endwall region is sensitive to the variation of endwall boundary layer. The wall vortex and the trailing edge vortex contribute much in cascade losses, while the passage vortex which transfers low energy fluid away from the endwall only produces a small amount of loss in the original scheme. The shedding vortex is obviously suppressed in the streamwise suction slot schemes as both the secondary transition of endwall boundary layer and corner region separation are under control. The development of passage vortex is most effectively controlled in the suction scheme which transfers part of inlet boundary layer away from the cascade. 

Key words: High-turning compressor cascade; Boundary layer suction; Secondary flow; Vortex structure; Flow loss; Suction position

摘要： 为探明附面层抽吸技术对压气机叶栅气动性能的影响及其与栅内旋涡结构的关联,通过十个横截面的实验测量结果研究了高负荷压气机叶栅抽吸端壁附面层前后的主要旋涡结构以其对应损失的演变过程。研究对象为矩形低速扩压叶栅,来流马赫数约为0.23。研究结果表明,端壁附面层的变化对叶栅端区的主要旋涡发展过程影响显著。在原型方案中,壁面涡、尾缘脱落涡的演变过程对应着较高的流动损失,通道涡自身产生的损失较小,主要起到向远离端壁的方向输运低能流体的作用；在流向槽吸气方案中,壁面涡和尾缘脱落涡因端壁附面层径向迁移及角区分离受到抑制而被明显削弱；而来流附面层抽吸方案则最为有效地控制了通道涡的演变过程。 

关键词: 大转角扩压叶栅;附面层抽吸;二次流动;旋涡结构;流动损失;抽吸位置 