具有叶尖小翼的涡轮叶栅间隙流动的实验研究  

Experimental Investigation on Tip Clearance Flow of a Turbine Cascade with Tip Winglet

作　　者：魏曼[1] 钟兢军[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》2015年第12期1825-1832,共8页Journal of Propulsion Technology

基　　金：中央高校基本科研业务费专项资金资助(3132014319);辽宁省高等学校创新团队支持计划资助(LT2015004)

摘　　要：涡轮动叶叶顶间隙流动是引起动叶内部流动损失的重要因素之一,大约30%的流动损失是由间隙流动引起的。对高负荷涡轮叶栅在间隙高度1%叶高、0°冲角的条件下,加装不同宽度和安装位置的叶尖小翼进行了实验研究,结果表明,压力面小翼在一定程度上削弱了泄漏涡强度,0.3倍叶片当地厚度的压力面小翼效果最佳。吸力面小翼可使泄漏涡运动轨迹向相邻叶片的压力面侧偏移、泄漏涡强度减弱,间隙泄漏损失降低。随着吸力面叶尖小翼宽度的不断增加,叶尖小翼对泄漏流动的控制作用也不断增强,当宽度在1.2倍叶片当地厚度时,对泄漏流动控制效果最好,可使叶栅测量截面总损失与不加小翼的叶栅相比降低28%。组合小翼不如单纯的吸力面小翼效果好。Tip leakage flow is one of the most influential features of the flow through turbine rotor,which is responsible for as much as 30 % of the total aerodynamic losses. A detailed experimental study has been carried out to investigate the effect of blade tip winglet with different installation positions and different widths on the performance of a turbine cascade,under 1% blade height tip clearances,0°angle of attack. Experimental results show that,for the cases with pressure-side winglet,the strength of tip leakage vortex can be reduced and the optimal winglet width is 0.3 times of the local blade thickness. For the cases with suction-side winglet,the tip leakage vortex trajectory shifts toward the pressure surface of the adjacent blade. Moreover,the strength of tip leakage vortex and the tip leakage loss are reduced. As the winglet width increases,the effects of the suction-side winglet on leakage flow are enhanced. The optimal winglet width is about 1.2 times of the local blade thickness and the total pressure loss of the cascades measuring section is reduced by about 28% when compared with the baseline tip blade. The influence of combined winglet case is not as effective as suction-side winglet case.

关 键 词：涡轮叶栅 间隙泄漏流动 叶尖小翼 实验研究 

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]