Effect of blade tip winglet on the performance of a highly loaded transonic compressor rotor

作     者：Han Shaobing Zhong Jingjun 

作者机构：Marine Engineering CollegeDalian Maritime University 

出 版 物：《Chinese Journal of Aeronautics》 (中国航空学报（英文版）)

年 卷 期：2016年第29卷第3期

页      面：653-661页

核心收录：

学科分类：08[工学] 082502[工学-航空宇航推进理论与工程] 0802[工学-机械工程] 0825[工学-航空宇航科学与技术] 0801[工学-力学（可授工学、理学学位）] 

基　　金：co-supported by the National Natural Science Foundation of China(Nos.51436002,51406021) the Scientific Research Fund of Education Department of Liaoning Province(No.L2014197) the Program for Liaoning Innovative Research Team in University(No.LT2015004) the Fundamental Research Funds for the Central Universities(Nos.3132016014,3132014319) 

主　　题：Blade tip winglet Numerical study Shock wave/tip leakage vor-tex interaction Stall range Tra,asonic compressor rotor 

摘      要：The tip leakage flow has an important influence on the performance of transonic com- pressor. Blade tip winglet has been proved to be an effective method to control the tip leakage flow in compressor, while the physical mechanisms of blade tip winglet have been poorly understood. A numerical study for a highly loaded transonic compressor rotor has been conducted to understand the effect of varying the location of blade tip wing]et on the performance of the rotor. Two kinds of tip winglet were designed and investigated. The effects of blade tip winglet on the compressor over- all performance, stability and tip flow structure were presented and discussed, It is found that the interaction of the tip winglet with the flow in the tip region is different when the winglet is located at suction-side or pressure-side of the blade tip. Results indicate that the suction-side winglet （SW） is ineffective to improve the performance of compressor rotor. In addition, a significant stall range extension equivalent to 33.74% with a very small penalty in efficiency can be obtained by the pressure-side winglet （PW）. An attempt has been made to explain the fundamental mechanisms of blade tip winglet in detail.