深凹槽式涡轮叶顶间隙泄漏直列叶栅实验研究  

Experiment Research on Deep Double Squealer Tip Clearance Leakage Flow in Linear Turbine Cascade

作　　者：崔涛[1] 陈绍文[1] 周治华[1] 王晋声[1] 王松涛[1] 王仲奇[1] 

机构地区：[1]哈尔滨工业大学能源科学与工程学院,哈尔滨150001

出　　处：《工程热物理学报》2015年第9期1902-1906,共5页Journal of Engineering Thermophysics

基　　金：国家自然科学基金创新研究群体项目(No.51121004);国家自然科学基金项目(No.51206035)

摘　　要：在低速风洞实验台,对具有不同深凹槽结构平面叶栅在不同间隙尺度条件下的流动特性进行了实验研究。实验采用五孔气动探针和高灵敏度及高精度的压力扫描阀测量了叶栅出口截面的气动参数,对比分析了总压损失的展向分布,并在叶栅端壁和叶片表面进行墨迹显示。结果表明,深凹槽式叶顶结构应用于本文研究的叶栅上是可行的。深凹槽尾缘开口有利于降低叶顶间隙泄漏损失,凹槽前缘开口对前缘附近局部流动产生一定影响。对整个流动通道涡生成影响不如泄漏流作用强,并且尾缘开口与前缘开口开度的匹配对叶顶间隙泄漏损失有明显的影响。Experiment research was carried out on the tip clearance leakage flow characteristics of a linear turbine cascade in a low-speed wind tunnel with a series of deep double squealer at three kind of clearance. Theaerodynamics parameters were measured at outlet by a five-hole probe with high resolution and precisionto comparelyanalyse the flow characteristics and the distribu- tion ofspan normalized loss, beyond that the Ink-Trace flow visualization was carried out on the cascade surface and the upper endwall. The results prove that the deep double squealer tip is applicable. Pressure Side squealercutted near the trailing edge makes contributions to the decrease of leakage loss, while squealer cutted near the leading edge only have a little influence on the leading upper endwall locally. The whole passage vortex is mainly affected by the leakage flow. The cutted size match between near the leading and trailing edge will strongly influencethe leakage loss.

关 键 词：深凹槽 间隙间隙流动 涡轮 实验研究 

分 类 号：TK47[动力工程及工程热物理—动力机械及工程]