Numeca CFDcommercial software was used to simulate numerically the flow field of a high-turning cascade and axial compressor.In order to mitigate the loss from boundary layer separation and expand the working range

a proposal for slot suction on blade suction surface was presented.The influences of position of slots

length of slots and the mass flow of suction on the separation structure and stall margin were investigated.The results show that

the aerodynamic performance could be improved significantly through release of low-energy air current at upstream boundary layer of stator blade

and the flow separation could also be postponed with improved stall margin.