关键词: 压气机叶栅;角区分离;通道涡;端壁;附面层抽吸

Abstract: A high load compressor cascade with boundary layer suction(BLS) at end-wall has been investigated by numerical simulation to explore a better way to control the corner separation.The effects of two schemes of different BLS location to the cascade performance,flow structure of corner and passage vortex have been analyzed.The results show that when the suction slot is located 5% C(chord) upstream of leading edge,onset of the passage vortex is decayed due to the boundary layer suction.However,the inlet flow angle has been changed,which lead to separation vortex happening near the cascade corner.In addition,the interaction of the separation vortex and the passage vortex deteriorates the flow structure,which increases the deviation angle and the total pressure loss.When the suction slot is located at 25% C downstream of the cascade leading edge,BLS removes the higher entropy flow near the end-wall,which may restrict the development of passage vortex,ameliorate the flow structure of cascade passage and decrease the total pressure loss.Moreover,it does not affect the upstream flow field.However,there is a higher total pressure loss area between the cascade corner and main stream flow when the suction slot is located at 25% C because the separating flow near the corner is not eliminated absolutely.

Key words: Compressor cascade;Corner separation;Passage vortex;End-wall;Boundary layer suction