摘要
本文提出一个无粘的底部压力模型。证明了在给定反压的情况下,超音出口的涡轮叶栅的叶片尾缘的底压以及叶型损失可由该模型确定。与无粘的流场计算相结合,可用该模型计算二维叶栅的底压。对模型的参数研究表明:具有正曲率的喉道下游叶背型面将有利于减少损失;而出口为音速时流动则最为不利。
An inviscid base pressure model for transonic turbine blade is presented It is shown that for a given back pressure the base pressure at the trailing edge and the profile toss of the blade are fixed and the base pressure can be calculated using an inviscid numerical scheme. A parametric study shows that positive curvature downstream of the throat is advantageous for generating less loss.An inviscid base pressure model for transonic turbine blade is presented It is shown that for a given back pressure the base pressure at the trailing edge and the profile toss of the blade are fixed and the base pressure can be calculated using an inviscid numerical scheme. A parametric study shows that positive curvature downstream of the throat is advantageous for generating less loss.
出处
《力学学报》
EI
CSCD
北大核心
1991年第4期393-399,共7页
Chinese Journal of Theoretical and Applied Mechanics
关键词
跨音速透平
叶栅
底压
无粘模型
base pressure, transonic turbine, trailing edge loss
