To avoid compressor stall, a numerical simulation method was used to investigate the fanshaped cascade of the transonic compressor DMU37 stator blade, and analyze the performance of the fan cascade when the end wall of the cascade and the suction surface were simultaneously suctioned by the boundary layer, as well as discussing the effect of changing the total suction mass flow rate. It is concluded that the loss in the end wall area will gradually decrease with the increase of the suction flow, and the backflow strength in the threedimensional corner area of the upper and lower end walls will be weakened. The flow capacity increases gradually with the increase of suction flow, and the main vortex structure in the cascade gradually migrates to the end wall. As the suction flow rate increases, the velocity of the fluid flowing into the suction chamber increases and the suction capacity of the attached surfaces layer increases. When the suction mass flow rate is 2% of the inlet flow, the total pressure loss coefficient is reduced by 49.07% compared with that without suction. Under the condition of a fixed suction flow rate, the combined suction of doublesided end wall suction and suction surface can make the aerodynamic parameters of the cascade more uniform and delay the separation of the boundary layer. To analyze the effect of the combined surface layer suction on the separation of the angular area of the fan blade cascade from the profile, and to further investigate the mechanism of combined surface layer suction can provide a theoretical basis and design criteria for the application of surface layer suction in compressors and the design of adsorption compressors.