Abstract: To explore the effects of boundary layer suction on aerodynamic performance and flow field structure in a subsonic highly-loaded sectorial compressor cascade， a research that streamwise groove boundary layer suction on the lower endwall， was completed by the method of numerical simulation. The improvement of different suction schemes was compared. The results show that the separation and back-flow in lower corner has been effectively restrained， the total pressure loss around the lower corner has been decreased and the diffusion capacity near lower endwall has been enhanced after the suction on lower endwall， but the separation in upper corner is slightly strengthened. The suction scheme with the groove starting slightly downstream the separation point of the corner region (EW2) is the best when the suction flow is 0.50% of the mass flow rate of the original cascade. The overall total pressure loss of cascade is reduced by 27.65%， and the static pressure ratio increased by 8.69%.

Key words: Endwall；Streamwise groove suction；Highly-loaded；Sectorial compressor cascade；Aerodynamic performance

摘要： 为探究附面层抽吸对亚声速高负荷扇形扩压叶栅气动性能和流场结构的影响，利用数值方法对叶栅进行了下端壁流向槽附面层抽吸的研究。对比原型和各抽吸方案发现:下端壁附面层的抽吸可以有效抑制下角区低能流体的分离及回流，降低下角区总压损失并提升叶栅近端壁区域的扩压能力，但上角区分离会略有加剧。当抽吸质量流量为原型叶栅质量流量的0.50%时，抽吸槽起始于角区分离点下游附近的抽吸方案(EW2)效果最佳，叶栅整体总压损失降低27.65%，静压比提升8.69%。

关键词: 端壁；流向槽抽吸；高负荷；扇形扩压叶栅；气动性能