跨音涡轮叶栅底压的无粘模型  

AN INVISCID MODEL FOR THE BASE PRESSURE OF TRANSONIC TURBINE CASCADE

作　　者：徐力平[1] 

机构地区：[1]北京航空航天大学

出　　处：《力学学报》1991年第4期393-399,共7页Chinese Journal of Theoretical and Applied Mechanics

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.

关 键 词：跨音速透平 叶栅 底压 无粘模型 

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]