压力面小翼对涡轮叶栅不同间隙下流场影响的实验  

Experiment on effect of pressure-side winglet on flow field in turbine cascade at different tip clearances

作　　者：钟兢军[1] 魏曼[1] 陆华伟[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：《航空动力学报》2016年第1期84-91,共8页Journal of Aerospace Power

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

摘　　要：对某涡轮叶栅加装不同宽度的压力面小翼对叶栅间隙流场的影响进行了实验研究,详细测量了间隙高度为0.5%h,1%h,1.5%h时叶栅出口流场和叶片表面静压分布情况.通过实验结果分析得出:随着间隙高度的增加,间隙泄漏流动加剧,泄漏涡增强,叶栅总损失增加,同时使上通道涡的强度减弱;压力面小翼在间隙高度为0.5%h时对间隙泄漏流动的控制效果较好,宽度为0.4倍当地叶片厚度的压力面小翼能使叶栅总损失降低18%.间隙高度为1%h时,0.3倍当地叶片厚度的压力面小翼效果最佳,使叶栅总损失降低10.37%.间隙高度为1.5%h时,压力面小翼对间隙泄漏流动基本没有影响,但在一定程度上降低了叶栅总损失.Detailed experiments were carried out to investigate the effect of the tip clear- ance flow in a turbine cascade with different width pressure-side winglets. The flow field of the cascade outlet and the static pressure distribution on the blade surface were surveyed in detail at different tip clearance height of 0.5%h, 1%h, 1.5%h. The results show that, as the tip clearance height increases, the leakage flow is intensified, the leakage vortex is strengthened, the total loss of cascade is increased, and the up channel vortex is weakened. Pressure-side winglet has a good effect at the 0.5%h tip clearance height, the total loss of the cascade is reduced by 18% with width being 0.4 times of the local blade thickness. 0. 3 times of the local blade thickness case reduces the total loss of the cascade by 10.37 % at the 1%h tip clearance height. At the 1.5%h tip clearance height, the pressure-side winglet al- most has no effect on clearance leakage flow, but reduces the total loss of the cascade to a certain extent.

关 键 词：涡轮叶栅 间隙高度 压力面小翼 间隙泄漏流动 实验测量 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]