压力面小翼对涡轮叶栅不同冲角下流场影响的实验研究  

Experimental Investigation of Different Pressure-Side Winglets on Tip Clearance Flow in a Turbine Cascade with Different Incidences

作　　者：钟兢军[1] 魏曼[1] 

机构地区：[1]大连海事大学轮机工程学院,辽宁大连116026

出　　处：《推进技术》2016年第5期892-899,共8页Journal of Propulsion Technology

基　　金：国际自然科学基金重点项目(51436002);中央高校基本科研业务费专项资助(3132014319);辽宁省高等学校创新团队支持计划资助(LT2015004)

摘　　要：为了控制和降低涡轮动叶由叶顶间隙所引起的泄漏损失,对加装不同宽度压力面小翼的涡轮叶栅间隙流场进行了实验研究,详细测量了±10°,±5°,0°冲角时涡轮叶栅出口流场和叶片表面静压分布情况。结果表明:随来流冲角由负到正,泄漏涡强度减弱,泄漏损失降低;通道涡强度增强,其引起的损失增大。压力面小翼在不同冲角下均对叶顶泄漏流动具有一定的控制作用,在设计冲角和较小的正冲角工况下PW0.3方案压力面小翼作用效果较好,分别使叶栅总损失降低10.38%和8.11%。在冲角变化范围更大时,PW0.4方案压力面小翼效果更好。To control and reduce the leakage loss of the rotor by the tip clearance, detailed experiments have been carried out to investigate the effect of the tip clearance flow in a turbine cascade with different width of pressure-side winglets. The flow field of the cascade outlet and the static pressure distribution on the blade surfac-es have been detailed surveyed with different incidences （±10°,±5°,0°） . The results show that,as the inci-dences change from negative to positive,the leakage vortex weaken and the leakage loss decreases,the passage vortices and their losses are strengthened. Pressure-side winglet has a certain effect with all different incidences. The PW0.3 scheme is the best with the design and the smaller incidence , it can make the total loss of the cas-cade reduced 10.38%and 8.11%.As the change to the incidence range is larger, the PW0.4 scheme＇s effect is better.

关 键 词：涡轮叶栅 冲角 压力面小翼 间隙泄漏流动 实验测量 

分 类 号：V235.1[航空宇航科学与技术—航空宇航推进理论与工程]