This study seeks to evaluate the effects of profile variability on the aerodynamic per-formance of a compressor and provide guidance for the robust design of compressor blades.

A mathematical model of profile variability distribution with a single peak is established. The effects of the combined profile variability of the blade pressure and suction surface on the aerodynamic performance of two supersonic planar cascades are then investigated by numerical simulation.

The results show that the profile variability distribution on the suction surface is the key factor behind cascade total pressure loss. The total pressure loss coefficient decreases gradually with the position of maximum profile variability on the suction surface moving downstream. The profile variability distribution on the blade pressure and suction surface influences the flow turning angle and static pressure rise coefficient with opposite trends. The profile variability on the suction surface plays a dominant role in the flow turning angle and static pressure rise of cascade with lower incoming Mach number; for cascade with higher incoming Mach number, the profile variability on the pressure surface has a significant impact on the flow turning angle and static pressure rise. The position and intensity of the shockwave and the end wall profile of the expansion channel after the shockwave comprehensively determine the flow state on the blade surface and in the cascade blade passage. The flow loss near the blade suction surface increases, the flow loss near the blade pressure surface decreases, and the compound effect determines the change of cascade loss, flow turning angle and static pressure rise.

The results of this study can provide guidance for the design, manufacture and manufacturing variability evaluation of transonic compressors.