Abstract: Boundary layer suction can control the flow separation in the compressor cascade and increase the aerodynamic load of the cascade. To investigate the influence of the arrangement of suction slots on the aerodynamic performance of the compressor cascade, blowing experiments were carried out in the transonic wind tunnel of the Engine Aerodynamic Research Center of Harbin Institute of Technology. At the same time, the numerical simulation of the cascade was carried out. The results show that the endwall boundary layer suction can effectively reduce the total pressure loss of cascades. The effect of boundary layer suction is related to the number of suction slots.