Effects of blade profile on corner separation in compressor cascade

Effects of suction surface corner separation on the aerodynamic performance and effects of the blade parameters on suction surface corner separation in linear compressor cascade were researched to prevent corner separation when designing profile. Static pressure on suction surface was changed, and a C-Shape pressure distribution along span wise was built owing to corner separation. The C-Shape pressure distribution of closed separation is much more significant than that of open separation. Stream wise adverse pressure gradient after the lowest pressure point on suction surface of closed separation is larger than that of open separation. Diffusion capability decreases and loss increases because of the separation, aerodynamic performance degradation of closed separation is larger than that of open separation. Results show that corner separation is influenced by profile parameters significantly, with the increase of the blade thickness, the maximum thickness position moving afterwards and the deflection of mean camber line, the curvature gradient after the max blade thickness position of suction surface increases, the stream wise adverse pressure gradient on the suction surface after the lowest pressure point increases, the scale of separation zone increases, even the separation form could change from open separation to closed separation.