基压对跨声速涡轮叶栅尾迹损失影响的研究  

Base Pressure Influence on the Trailing Edge Loss of Transonic Turbine Cascade

作　　者：姜正礼[1] 凌代军[1] 

机构地区：[1]中国燃气涡轮研究院,四川江油621703

出　　处：《燃气涡轮试验与研究》2007年第3期23-27,共5页Gas Turbine Experiment and Research

基　　金：航空科学基金资助项目(04C24004)

摘　　要：跨声速涡轮尾迹损失是叶栅损失的主要部分,大约占总损失的三分之一。跨声速尾迹气流十分复杂,必须了解其基本的气流流动模型。目前,计算损失的方法大多根据经验公式,但该方法限制了计算损失的准确性。国外一些研究表明:基压与损失、基压与反压都存在着一定的关系。本文利用超、跨声速平面叶栅风洞在近二十年中所做的叶栅试验数据,进行分类整理,总结出基压对反压和基压对损失的简便经验公式,为叶型设计的气动计算提供叶栅损失系数和叶片表面马赫数分布的预估。Trailing edges loss is one of the main sources of loss for transonic turbine cascade, contributing typically 1/3 of their total loss. Transonic trailing edge flow is extremely complex; the basic flow pattern is understood, but method predicting losses is currently based on empirical correlations for the base pressure. These correlations are of limited accuracy. Many recent investigations indicated that there is a unique relationship between the base pressure and loss; the base pressure and backpressure. In this paper, the empirical correlations of the base pressure with backpressure and base pressure with cascade loss were summarized by means of cascade experimental data in the past two decades.

关 键 词：基压 跨声速平面叶栅 叶栅尾迹损失 

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]