变冲角下压力面小翼控制高亚声速扩压叶栅气动特性的研究  

Effects of Pressure Side Winglet on Aerodynamic Performance of High Subsonic Compressor Cascade with Different Incidences

作　　者：吴宛洋 钟兢军[1] 韩少冰[1] 

机构地区：[1]大连海事大学轮机工程学院,辽宁大连116026

出　　处：《推进技术》2018年第1期76-85,共10页Journal of Propulsion Technology

基　　金：国家自然科学基金(51436002;51406021);中央高校基本科研业务费专项资金资助(3132016014;3132017001);辽宁省高等学校创新团队支持计划(LT2015004);辽宁省博士科研启动基金(201601078)

摘　　要：为了探究变冲角时压力面小翼对高亚声速扩压叶栅气动特性的影响,采用数值模拟软件ANSYS CFX对不同来流冲角下(0°,±3°,±6°)原型叶栅及加装了不同宽度压力面小翼的改型叶栅进行了数值计算。结果表明:不同冲角下压力面小翼都可以削弱泄漏涡的强度,改善叶顶间隙流动,降低叶栅流动损失。不同冲角时具有不同的最佳小翼方案,PW1.5方案在+6°冲角下性能提高最大,与同冲角下的原型叶栅相比,PW1.5方案的总压损失降低了14.4%。In order to investigate the effects of the pressure side winglet on aerodynamic performance of high subsonic compressor cascade under different angles of incidence,the numerical simulation has been carried out to explore the original cascade and cascades with different pressure side winglets at different incidences（0°,±3°,±6°）by using the ANSYS CFX software. The results show that the pressure side winglet can reduce the intensity of tip leakage vortex and improve the tip clearance flow at different incidences,thus the total pressure loss of the cascade is decreased. The best winglet scheme is changing with the various angles of incidence,and the most effective pressure side winglet is PW1.5 at angle of ＋6°,which provides the most significant aerodynamic loss reduction by 14.4% compared to original cascade at the same incidence.

关 键 词：压气机叶栅 压力面小翼 冲角 数值模拟 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]