叶尖小翼控制压气机间隙流动的研究进展  

Research Progress of Compressor Tip Leakage Flow Control Using Blade Tip Winglet

作　　者：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》2017年第10期2200-2207,共8页Journal of Propulsion Technology

基　　金：国家自然科学基金(51436002;51406021);辽宁省高校创新团队支持计划(LT2015004);辽宁省博士科研启动基金项目(201601078);中央高校基本科研业务费专项资金(3132017001;3132016334)

摘　　要：综述了叶尖小翼控制压气机叶顶间隙泄漏流动的研究进展。首先介绍了叶顶泄漏流动对压气机气动性能的影响,接着回顾了叶尖小翼技术在涡轮中的研究概况,之后详细介绍了大连海事大学船舶动力工程研究所在压气机叶尖小翼技术方面开展的一系列研究工作,分别讨论了叶尖小翼对压气机矩形叶栅、亚声速压气机转子和跨声速压机转子气动性能的影响及其作用机制。最后给出了压气机叶尖小翼技术未来的发展方向和研究前景。Review on research progress of compressor tip leakage flow control using blade tip winglet was presented. The effects of tip leakage flow on the aerodynamic performance of compressor were described firstly.After then,review on the research of blade tip winglet in turbine was presented. A series of research works of compressor blade tip winglet carried out by Institute of Ship Power Engineering of Dalian Maritime University were introduced. Furthermore,the effects of blade tip winglet on the aerodynamic performances of compressor cascade,subsonic compressor rotor and transonic compressor rotor were briefly summarized. The research prospect of compressor blade tip winglet was also presented.

关 键 词：叶尖小翼 压气机 间隙流动 泄漏涡 

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]