融合式叶尖小翼对低速压气机转子气动性能的影响

推进技术 ›› 2014, Vol. 35 ›› Issue (6): 749-757.

融合式叶尖小翼对低速压气机转子气动性能的影响

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(1963—)，男，教授，研究领域为叶轮机械气动热力学。E-mail:zhongji@dlmu.edu.cn
基金资助:
国家自然科学基金项目(51076018)；中央高校基本科研业务费专项资金资助项目。

Effects of Blended Tip Winglet on Aerodynamic Performance of a Low Speed Compressor Rotor

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

Published:2021-08-15

摘要/Abstract

摘要： 为了进一步揭示融合式叶尖小翼对压气机转子间隙流动的影响机理，采用数值模拟方法对低速压气机转子加装叶尖小翼控制间隙流动进行研究，着重考察了不同几何宽度及安装方式小翼对转子气动性能的影响。结果显示，叶尖小翼改变了转子中的泄漏涡轨迹，影响着叶片吸力面附面层的分离程度，适当几何宽度的压力面小翼可以在压气机转子效率略有降低的情况下使其失速点流量系数减小8.20%。

关键词: 融合式叶尖小翼；低速压气机转子；间隙流动；数值研究

Abstract: In order to further reveal the effects and action mechanics of the blended winglet on the tip leakage flow of compressor rotor，a numerical simulation has been carried out to investigate the effects of blade tip winglet on controlling tip clearance flow in an axial compressor rotor. Emphasis was put on the analysis of effectiveness of blade tip winglet with different winglet geometries，suction side winglet and pressure side winglet. The simulation results show that rotor tip leakage vortex trajectories are changed by the blended tip winglets. Thus the degree of suction surface boundary layer separation is also changed. The specific pressure side winglet is found highly effective to reduce the compressor rotor stalling flow coefficient by 8.20% with a slight reduction of efficiency.

Key words: Blended tip winglet；Low speed compressor rotor；Tip leakage flow；Numerical simulation

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.

参考文献

[1] 陈懋章. 压气机气动力学发展的一些问题 [ J ] . 航空学报，1985， 6(5): 405-410.
[2] Lu X， Chu W， Zhu J， et al. Numerical Investigation of the Coupled Flow Through a Subsonic Compressor Rotor and Axial Skewed Slot [ J ] . ASME Journal of Turbomachinery ，2009， 131(1).
[3] Suder K L， Hathaway M D， Thorp S A. Compressor Stability Enhancement Using Discrete Tip Injection [ J ] . ASME Journal of Turbomachinery ， 2001， 123(1): 14-23.
[4] Vo H D. Suppression of Short Length-Scale Rotating Stall Inception With Glow Discharge Actuation [ R ] . ASME 2007- GT -27673.
[5] Ramakrishna P V， Govardhan M. Stall Characteristics and Tip Clearance Effects in Forward Swept Axial Compressor Rotors [ J ] . Journal of Thermal Science ， 2009， 18(1): 40-47.
[6] Ma H， Li B. Effects of Axial Non-uniform Tip Clearance on Aerodynamic Performance of a Transonic Axial Compressor [ J ] . Journal of Thermal Science ， 2008， 17(4): 331-336.
[7] 钟兢军，韩吉昂，严红明，等. 压气机动叶叶尖小翼 [ P ] . 中国专利: ZL 200810010515. 4，2010-06-09.
[8] Zhong J， Han S， Sun P. The Influence of Suction-Side Winglet on Tip Leakage Flow in Compressor Cascade [ R ] . ASME 2011- GT -46054.
[9] Han S， Zhong J， Lu H， et al. Experimental Investigation on Tip Clearance Flow of Compressor Cascade with Blade Tip Winglet [ R ] . ASME 2012- GT -69226.
[10] 韩少冰，钟兢军. 变冲角下吸力面小翼对压气机叶栅气动性能的影响 [ J ] . 推进技术， 2012，33(3): 384-390. (HAN Shao-bing， ZHONG Jing-jun. Effects of Suction-Side Winglet on Aerodynamic Performance of Compressor Cascade at Different Incidence [ J ] . Journal of Propulsion Technology ， 2012，33(3): 384-390. )
[11] 邓向阳. 压气机叶顶间隙流的数值模拟研究 [ D ] . 北京:中国科学院研究生院，2006.
[12] 马宏伟，蒋浩康. 压气机设计状态转子出口及下游三维紊流流场 [ J ] . 燃气涡轮试验与研究， 1998，11(2):31-35.
[13] 杜娟. 跨音压气机/风扇转子叶顶泄漏流动的非定常机制研究 [ D ] . 北京: 中国科学院研究生院， 2010.
[14] Khalid S A， Khalsa A S， Waitz I A， et al. Endwall Blockage in Axial Compressor [ J ] . ASME Journal of Turbomachinery ， 1999， 121(3): 499-509.
[15] 马宏伟，蒋浩康. 单转子压气机设计状态和近失速状态出口三维紊流流场 [ J ] . 工程热物理学报， 1997， 18(2):153-158.
[16] 卢新根，楚武利，朱俊强，等. 梯状间隙结构对轴流压气机影响的试验与数值模拟 [ J ] . 工程热物理学报， 2005，26(2): 234-236.
[17] Lakshminarayana B B，Horlock J H. Leakage and Second Flows in Compressor Cascades [ R ] . British ARC R&M 3483， 1967.
[18] Vo H D， Tan C S， Gretizer E M. Criteria for Spike Initiated Rotating Stall [ R ] . ASME 2005- GT -68374.
[19] Camp T R， Day I J. A Study of Spike and Modal Stall Phenomena in a Low-Speed Axial Compressor [ J ] . ASME Journal of Turbomachinery ， 1998， 120(3): 393-401.
[20] Takahiro N，Toshio K，Hiroshi H. Rotor-Tip Flow Fields near Inception Point of Modal Disturbance in an Axial-Flow Fan [ R ] . ASME 2010- GT -22187.