Influence of Endwall Air Injection with Discrete Holes on Corner Separation of a Compressor Cascade  

作　　者：CAO Zhiyuan GAO Xi ZHANG Xiang ZHANG Fei LIU Bo 

机构地区：[1]School of Power and Energy,Northwestern Polytechnical University,Xi’an,710072,China

出　　处：《Journal of Thermal Science》2021年第5期1684-1704,共21页热科学学报（英文版）

基　　金：This work was sponsored by the seed Foundation of Innovation and Creation for Graduate Students in Northwestern Polytechnical University(No.CX2020138);National Natural Science Foundation of China(Nos.51806174 and 51741601);the Fundamental Research Funds for the Central Universities of China(No.G2018KY0303).

摘　　要：The aim of this study is to reveal the influence mechanism of endwall air injection with distributed holes on the corner separation of a highly loaded compressor cascade,so as to promote the application of injection in aero-engines.Single-hole and double-hole endwall injection schemes featuring different axial locations,pitchwise locations,injection mass rates and injection directions,were designed and investigated.Results showed that the corner separation was eliminated by endwall injection;the optimal single-hole injection scheme achieved an endwall loss coefficient reduction of 29.7%,with injection coefficient as low as 0.48%.The optimal axial location of single-hole endwall injection was at 82%axial chord,being the center of corner separation.However,as injection hole was located at upstream of it,endwall injection resulted in severer corner separation.The mid-span flow field was deteriorated after endwall injection,which was due to 3D flow effects,i.e.,AVDR(axial velocity density ratio)effect and low-momentum fluid spanwise migration effect.The optimal injection was achieved at low injection angle and from close to the suction surface on pitchwise.Double-hole injection exhibited inferior performance compared with single-hole,which was due to the interaction of the two injection streams and mixing of injection streams with the bulk stream.

关 键 词：compressor cascade corner separation flow control air injection endwall discrete hole injection 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]