变攻角下低压涡轮导向器二次流的实验研究  

Experimental Investigation of Secondary Flow with Different Incidences in an LP Turbine Guide Vane

作　　者：陈绍文[1] 陈浮[1] 徐文远[1] 王仲奇[1] 

机构地区：[1]哈尔滨工业大学,黑龙江哈尔滨150001

出　　处：《燃气涡轮试验与研究》2005年第4期15-19,共5页Gas Turbine Experiment and Research

基　　金：APTD计划资助项目(APTD-0402-04-03)

摘　　要：在低速扇形叶栅风洞上,对五种攻角下的某型低压涡轮导向器原型和改型叶栅进行了实验研究,详细测量了各攻角下叶栅流道内的流场,分析了二次流发生和发展的过程以及攻角对其的影响,并通过改型和原型叶栅的对比,讨论了减少二次流损失的机理。结果表明,改型叶栅有效地降低了端壁横向压力梯度和前缘逆压梯度,抑制了边界层增厚和分离,从而控制了漩涡的生成和发展,削弱了通道涡的强度和尺度,使得二次流损失减少。In a low speed sectorial cascade tunnel, an experimental study was carried out on tim LP turbine guide vane of original and modified designs at five incidences. The cascades＇ flow fields, the generation and development of vortices were surveyed and analyzed in detail at different incidences, and the effect of blade incidence on secondary flow was investigated. From the comparison of the experimental results of the original and modified designs, the mechanism of decreasing secondary flow losses were discussed. The results shown that the modification eliminated effectively the endwall crosswise pressure gradient and the leading edge negative pressure gradient, restrained the boundary layer thickness and separation near inlet and endwall, then controlled the generation and development of vortices,reduced the intensity and size of passage vortex, and decreased the secondary, flow loss,

关 键 词：航空、航天推进系统 实验研究 攻角 二次流 改型 

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]