大小叶片压气机平面叶栅试验研究  

EXPERIMENTAL INVESTIGATION OF SPLITTER COMPRESSORS IN A PLANAR CASCADE

作　　者：王洪伟[1] 蒋浩康[1] 陈懋章[1] 

机构地区：[1]北京航空航天大学航空发动机气动热力重点实验室,北京100083

出　　处：《工程热物理学报》2006年第z1期113-116,共4页Journal of Engineering Thermophysics

摘　　要：本文对大小叶片平面叶栅流动进行了详细的测量,初步分析了大小叶片设计优化规律.大叶片叶栅稠度1.3,小叶片尾缘与大叶片尾缘齐平且位于两大叶片尾缘正中.来流气流马赫数0.3,相应的基于大叶片弦长的雷诺数为7×105.测量结果显示:小叶片的存在降低了大叶片负荷,增强了大叶片抵抗分离的能力;随着攻角的增大,大叶片负载增大,而小叶片负载反而降低;大小叶片叶栅的落后角基本不随来流攻角变化,传统的落后角经验公式将不再适用.A planar cascade was setup to simulate the flow for splitter compressors.The test section has three flow passages that include four blades with three splitters.Inlet Mach number in the test is set to be 0.3,which gives a blade chord based Reynolds number of 7×10~5.The results show that: The presence of the splitters lowers the load on the blades and helps the blade to resist separation. The load on the blades increase and the load on the splitters decrease when angle of attack increases. Angle of lag does not vary with angle of attack,which suggests that the empirical equation for angle of lag calculating may not be suitable for the cascade with splitters.

关 键 词：大小叶片压气机 平面叶栅 流场测量 气动探针 表面压力测量 

分 类 号：TK474[动力工程及工程热物理—动力机械及工程]