叶尖小翼控制压气机间隙流动的研究进展

推进技术 ›› 2017, Vol. 38 ›› Issue (10): 2200-2207.

叶尖小翼控制压气机间隙流动的研究进展

钟兢军,韩少冰

大连海事大学轮机工程学院，辽宁大连 116026,大连海事大学轮机工程学院，辽宁大连 116026

发布日期:2021-08-15
作者简介:钟兢军，男，博士，教授，研究领域为叶轮机械气动热力学。
基金资助:
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

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

Marine Engineering College，Dalian Maritime University，Dalian 116026，China and Marine Engineering College，Dalian Maritime University，Dalian 116026，China

Published:2021-08-15

摘要/Abstract

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。

关键词: 叶尖小翼；压气机；间隙流动；泄漏涡

Abstract: 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.

Key words: Blade tip winglet；Compressor；Tip leakage flow；Tip leakage vortex

钟兢军,韩少冰. 叶尖小翼控制压气机间隙流动的研究进展[J]. 推进技术, 2017, 38(10): 2200-2207.

ZHONG Jing-jun,HAN Shao-bing. Research Progress of Compressor Tip Leakage Flow Control Using Blade Tip Winglet[J]. Journal of Propulsion Technology, 2017, 38(10): 2200-2207.

参考文献

[1] Freeman C. Tip Clearance Effects in Axial Turbomachines[R]. Von Karman Institute Lecture Series, 1985-05.
[2] Wisler D C. Aerodynamic Effects of Tip Clearance, Shrouds, Leakage Flow, Casing Treatment and Trenching in Compressor Design[R]. Von Karman Institute Lecture Series, 1985-05.
[3] Smith L H. The Effect of Tip Clearance on the Peak Pressure Rise of Axial-Flow Fans and Compressors[R]. ASME Symposium on Stall, 1958.
[4] Baghdadi. Modeling Tip Clearance Effects in Multistage Axial Compressors[J]. ASME Journal of Turbomachinery, 1996, 118(4): 697-705.
[5] Booth T C, Dodge P R. Rotor-Tip Leakage: Part Ⅰ-Basic Methodology[J]. ASME Journal of Engineering for Power, 1982, 104: 154-161.
[6] Wadia A R, Booth T C. Rotor-Tip Leakage: Part Ⅱ-Design Optimization Through Viscous Analysis and Experiment[J]. Journal of Engineering for Power, 1982, 104: 163-169.
[7] Yaras M I, Sjolander S A. Measurements of the Effects of Winglets on Tip-Leakage Losses in a Linear Turbine Cascade[R]. ISABE 91-7011.
[8] Harvey N W, Ramsden, K. A Computation Study of a Novel Turbine Rotor Partial Shroud[J]. ASME Journal of Turbomachinery, 2001, 123: 534-543.
[9] Dey D, Camci C. Tip Desensitization of an Axial Turbine Rotor Using Tip Platform Extensions[R]. Von Karman Institute Lecture Series, 2004-02.
[10] Saha A K, Acharya S, Bunker R, et al. Blade Tip Leakage Flow and Heat Transfer with Pressure-Side Winglet[J]. International Journal of Rotating Machinery, 2006, 19: 497-507.
[11] Kusterer K, Moritz N, Bohn D, et al. Reduction of Tip Clearance Losses in an Axial Turbine by Shaped Design of the Blade Tip Region[R]. ASME GT 2007-27303.
[12] Stephens J E, Corke T, Morris S C. Turbine Blade Tip Leakage Flow Control: Thick/Thin Blade Effects and Separation Line Studies[R]. ASME GT 2008-50705.
[13] Shavalikul A, Camci C. A Comparative Analysis of Pressure Side Extensions for Tip Leakage in Axial Turbines[R]. ASME GT 2008-50782.
[14] O’Dowd D O, Zhang Q, He L, et al. Aerothermal Performance of a Winglet at Engine Representative Mach and Reynolds Numbers[J]. ASME Journal of Turbomachinery, 2011, 133.
[15] Zhou C, Hodson H, Tibbott I, et al. The Aero-Thermal Performance of a Cooled Winglet Tip in a High Pressure Turbine Cascade[R]. ASME GT 2011-46369.
[16] Zhou C, Hodson H, Tibbott I, et al. Effects of Endwall Motion on the Aero-Thermal Performance of a Winglet Tip in a HP Turbine[R]. ASME GT 2011-46373.
[17] 钟兢军, 魏曼, 陆华伟. 压力面小翼对涡轮叶栅不同间隙下流场影响的实验[J]. 航空动力学报, 2016, 31(1): 84-91.
[18] 钟兢军, 魏曼. 压力面小翼对涡轮叶栅不同冲角下流场影响的实验研究[J]. 推进技术, 2016, 37(5): 892-899. (ZHONG Jing-jun, WEI Man. Experimental Investigation of Different Pressure-Side Winglets on Tip Clearance Flow in a Turbine Cascade with Different Incidences[J]. Journal of Propulsion Technology, 2016, 37(5): 892-899.)
[19] Tallman J A. A Computation Study of Tip Desensitization in Axial Flow Turbines[D]. Pennsylvania: The Pennsylvania State University, 2002.
[20] 韩少冰, 钟兢军, 陆华伟. 不同宽度吸力面小翼控制压气机叶栅间隙流动的实验研究[J]. 推进技术, 2016, 37(3): 471-478. (HAN Shao-bing, ZHONG Jing-jun, LU Hua-wei. Experimental Investigation of Compressor Cascade Tip Leakage Flow Control Using Suction-Side Winglet with Different Widths[J]. Journal of Propulsion Technology, 2016, 37(3): 471-478.)
[21] 韩少冰, 钟兢军. 带吸力面小翼的压气机叶栅变间隙特性实验[J]. 航空动力学报, 2016, 31(4): 847-856.
[22] 钟兢军, 韩少冰. 融合式叶尖小翼对低速压气机转子气动性能的影响[J]. 推进技术, 2014, 35(6): 749-757. (ZHONG Jing-jun, HAN Shao-bing. Effects of Blended Tip Winglet on Aerodynamic Performance of a Low Speed Compressor Rotor[J]. Journal of Propulsion Technology, 2014, 35(6): 749-757.)
[23] 韩少冰, 钟兢军, 杨凌, 等. 带压力面小翼的压气机转子叶顶间隙效应研究[J]. 工程热物理学报, 2014, 35(9): 1739-1743.
[24] 韩少冰, 钟兢军. 叶尖小翼对跨声速压气机转子变工况性能的影响[J]. 航空动力学报, 2016, 31(3): 647-658.
[25] Han Shaobing, Zhong Jingjun. Effect of Blade Tip Winglet on the Performance of a Highly Loaded Transonic Compressor Rotor[J]. Chinese Journal of Aeronautics, 2016, 29(3): 653-661.　　　　　　　　　　　　　*　收稿日期:2017-04-30；修订日期:2017-06-23。基金项目: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)。作者简介:钟兢军,男,博士,教授,研究领域为叶轮机械气动热力学。E-mail: zhongjj@dlmu.edu.cn(编辑:史亚红)