Effect of tip geometry and tip clearance on aerodynamic performance of a linear compressor cascade

查看全文 作　　者：Zhong [1]Jingjun;Han [1]Shaobing;Lu [1]Huawei;Kan [1]Xiaoxu

机构地区：[1]Marine Engineering College, Dalian Maritime University

出　　处：《Chinese Journal of Aeronautics》索引2013年第26卷第3期,共11页

基　　金：the National Natural Science Foundation of China(Grant No.:51076018);the Fundamental Research Funds for the Central Universities;Specialized Research Fund for the Doctoral Program of Higher Education 摘　　要：The tip leakage flow between a blade and a casing wall has a strong impact on compressor pressure rise capability, efficiency, and stability. Consequently, there is a strong motivation to look for means to minimize its impact on performance. This paper presents the potential of passive tip leakage flow control to increase the aerodynamic performance of highly loaded compressor blades. Experimental investigations on a linear compressor cascade equipped with blade winglets mounted to the blade tips have been carried out. Results for a variation of the tip clearance and the winglet geometry are presented. Current results indicate that the use of proper tip winglets in a compressor cascade can positively affect the local aerodynamic field by weakening the tip leakage vortex. Results also show that the suction-side winglets are aerodynamically superior to the pressure-side or combined winglets. The suction-side winglets are capable of reducing the exit total pressure loss associated with the tip leakage flow and the passage secondary flow to a significant degree. 关键词：线性压缩机叶尖间隙气动性能几何形状级联压气机叶片叶尖泄漏涡空气动力场

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Effect of tip geometry and tip clearance on aerodynamic performance of a linear compressor cascade

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