A method of using the blade end slot for passive control of the corner separation in a transonic compressor cascade was proposed. Because of the pressure difference between the pressure and suction sides

the blade end slot enables one to induce jet flow into the corner region

thereby restraining the corner separation in transonic cascade. The effect and mechanism of the blade end slot on the performance of the compressor cascade at different incidence angles were investigated numerically. The results demonstrate that

at smaller incidence angle

high-speed jet flow through the blade end slot can destroy the ring vortex in corner region

thereby reducing the corner separation

improving the performance of the cascade; at larger incidence angle

the jet flow can no longer destroy the ring vortex

but still re-energized the low-momentum fluid in the corner region

suppressed the corner separation

and the operation range was extended. The blade end slot reduced the total pressure loss coefficient by 11.6% at 0° incidence angle

and the operation range were increased from 2° to 3°.