End wall secondary flow control using vortex generator jet in compressor cascade with the turning angle of 60 degree was performed. The effects of variation of the direction and the total pressure of the jet on aerodynamic performance and flow of compressor cascade were presented. The results indicate that with the skew angle of 0 degree in vortex generator jet and jet mass flow rate less than 0.5% of inlet mass flow rate of compressor cascade

the loss of cascade could be reduced obviously. The vortex induced by the vortex generator jet could weaken or even prevent the development of passage vortex

make the fluid of the main stream involve into the end wall boundary layer in the down-washed region and guide the low energy fluid to the main stream in the up-washed region. Thus the accumulation of the low energy fluid in the corner region was reduced

resulting in the decrease of the separation on the suction surface. Using the same jet total pressure at inlet with that of the compressor cascade inlet

the reduction of 21.5% of total pressure loss can be obtained; this effect can become more obvious with the increase of the jet total pressure at inlet.