The detailed experimental investigations were carried out to analyze the effects of local boundary layer suction on aerodynamic performance of highly-loaded compressor cascade in low-speed condition.The exit aerodynamic parameters were measured by five-hole aerodynamic probe

and the distribution of the profile static pressure on the blade surface was obtained.The effects of local suction type

suction location and suction flow rate on the exit total pressure losses and load capacity of cascades were analyzed in detail.The results show that the effective low-energy fluid removal through side suction and middle suction on suction surface can increase the cascade load capacity

and effectively improve the cascade aerodynamic performance.The influence of the side suction on suction effectiveness is better than that of the middle suction.The cascade aerodynamic performance is obviously improved in the region of middle blade

but the improvement of the cascade aerodynamic performance is not clear near the end wall region.