A compressor end-modified cascade and its original cascade are compared experimentally to study the three-dimensional flow characteristics at the exit plane of the cascade.The results show that the modification of the end part at the trailing edge of the original blade (which is different from end-bend)would effectively improve the exit air angle spanwise distribution and meet the need of the inlet air angle of next row blades

on condition that the total pressure lose coefficient does not change or decrease.The test results also indicate that although the camber angle of the blades in the end part decreases due to the modification

the paseage-mass-averaged value of the camber angle changes few.Otherwise

the air flow through the cascade is the same to the original or even better.This technique has been successfully applied to improving both stall margin and efficiency of axial multistage compressors and to depressing the unsteady pressure disturbance.