关键词: 压气机;叶栅;翼刀;涡流发生器;角区分离;气动性能;失速

Abstract: To control the corner separation of compressor stator blades better， a new flow control method with little blades at the end wall of the leading edge of the passage were proposed， which combined the flow control idea of the end wall fence and the vortex generator. Taking a high-load axial compressor cascade as the research object， the influence of the little blades with different pitchwise positions and stagger angles on the flow field were analyzed in depth based on numerical methods. The results show that the little blades have the best pitchwise position and stagger angle range to improve the aerodynamic performance of the cascade. At the near stall condition， the little blades can alleviate corner separation and improve the diffuser capacity of the whole span， but inevitably increase the flow separation and the aerodynamic load near the middle of span. The little blades can reduce the corner separation loss and wake loss， and increase the static pressure coefficient at each axial cross section. The little blades can prevent the development of the pressure surface branch of horseshoe vortices and alleviate the cross secondary flow near the leading edge of the cascade. The induced vortices leaked from the tip of the little blades can push the pressure surface branch of horseshoe vortices toward the streamwise， take away the low-energy fluid near the end wall and corner area， thus weakening the strength of the passage vortices.

Key words: Compressor;Cascade;Fence;Vortex generator;Corner separation;Aerodynamic performance;Stall