带吸力面小翼的压气机叶栅变间隙特性实验

韩少冰; 钟兢军

doi:10.13224/j.cnki.jasp.2016.04.011

带吸力面小翼的压气机叶栅变间隙特性实验

doi: 10.13224/j.cnki.jasp.2016.04.011

大连海事大学轮机工程学院, 辽宁大连 116026

基金项目:

辽宁省高校创新团队支持计划(LT2015004)

中央高校基本科研业务费专项资金(3132015208,3132014319)

辽宁省教育厅科学研究一般项目(L2014197)

国家自然科学基金(51436002,51406021)

详细信息

作者简介:
韩少冰(1983-),男,河南驻马店人,讲师,博士,主要从事叶轮机械气动热力学方面的研究.

中图分类号: V231.3
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出版历程
- 收稿日期: 2015-10-26
- 刊出日期: 2016-04-28

Experiment on variable tip clearance characteristics of compressor cascade with suction-side winglet

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

摘要

摘要: 为了进一步揭示吸力面小翼在不同叶尖间隙条件下的影响机理,开展了有/无吸力面小翼的压气机叶栅变间隙特性实验.结果表明:与无间隙叶栅相比,叶尖相对间隙为1%时引入的泄漏流可以有效抑制叶片吸力面/端壁角区三维分离的产生,叶栅总损失和气动堵塞程度最低,此时为研究的4种间隙工况中的最佳间隙工况.吸力面小翼在此间隙下降低了泄漏涡强度的同时使通道涡增强,叶片吸力面重新出现了三维分离流动,叶栅总损失和堵塞程度均有所增加.在叶尖相对间隙为2%和3%时,带吸力面小翼叶栅中叶尖分离涡增强,主导叶尖区流动的泄漏涡强度减弱,两种间隙下叶栅总损失系数分别降低了8.9%和12.5%,堵塞系数分别降低了6.9%和6.3%.在研究的3种非零间隙条件下吸力面小翼降低了叶栅气动损失对叶尖间隙变化的敏感性,减弱了叶尖泄漏涡造成的叶栅出口气流角的欠偏转/过偏转程度.
- 吸力面小翼 /
- 压气机叶栅 /
- 变间隙特性 /
- 间隙泄漏流动 /
- 旋涡结构
Abstract: In order to further explore the effect mechanisms of suction-side winglet under different tip clearance sizes, an experimental investigation on the variable tip clearance characteristics of the compressor cascade with/without suction-side winglet was carried out. Results showed that at 1% relative tip clearance size, the tip leakage flow suppressed three-dimensional separation on the corner of suction surface and endwall, the cascade loss and endwall blockage were both minimum; and this clearance size was found to be optimum tip clearance. The suction-side winglet reduced the strength of tip leakage vortex but resulted in a stronger passage vortex, and the three-dimensional separation zone was formed again. For the particular tip clearance, the loss and endwall blockage of cascade with winglet were both higher than the baseline tip cascade. In case of 2% and 3% relative tip clearance sizes, for the cascade with suction-side winglet, the tip separation became stronger, and the strength of tip leakage vortex was reduced. In case of these two tip clearance sizes, the total pressure loss coefficients of the cascade was reduced by 8.9% and 12.5%, respectively by the suction-side winglet, and the blockage coefficients with winglet were 6.9% and 6.3% lower compared with the cascade without winglet. For these three tip clearance sizes, the compressor cascade performance sensitivity to tip clearance variation was improved by the suction-side winglet, and the degree of outlet flow angle's underturning and overturning induced by leakage vortex was reduced by the suction-side winglet.
- suction-side winglet /
- compressor cascade /
- variable tip clearance characteristics /
- tip clearance flow /
- vortical structure

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参考文献(26)

[1]	钟兢军,韩吉昂,严红明,等.压气机动叶叶尖小翼:中国,ZL200810010515.4[P].2010-06-09.
[2]	Tim H,Ivor D.Enhancing the stability of subsonic compressors using casing grooves[J].Journal of Turbomachinery,2011,133(2):021007.1-021007.11.
[3]	Mcnulty G S,Decker J J,Beacher B F.The impact of forward swept rotors on tip clearance flows in subsonic axial compressors[J].Journal of Turbomachinery,2004,126(4):445-454.
[4]	Wbitcomb R T.A design approach and selected wind-tunnel results at high subsonic speeds for wing-tip mounted winglets[R].NASA TN D-8260,1976.
[5]	Gomez G P,Gonzales-Adalid J.Tip loaded propellers justification of their advantages over conventional propellers using the momentum theory[J].International Shipbuilding Progress,1995,42(429):5-60.
[6]	杨振涛,汪建文,东雪青,等.小翼对风力机叶尖涡运动轨迹的影响研究[J].工程热物理学报,2012,33(12):2398-2401. YANG Zhentao,WANG Jianwen,DONG Xueqing,et al.Research on the influence of wind turbine vane tip vortex trajectory[J].Journal of Engineering Thermophysics,2012,33(12):2398-2401.(in Chinese)
[7]	Corsini A,Rispoli F,Sheard A G.Development of improved blade tip end-plate concepts for low-noise operation in industrial fans[J].Journal of Power and Energy,2007,221(5):669-681.
[8]	Shavalikul A,Camci C.A comparative analysis of pressure side extensions for tip leakage in axial turbines[R].ASME Paper GT2008-50782,2008.
[9]	Seo Y C,Lee S W.Tip gap flow and aerodynamic loss generation in a turbine cascade equipped with suction-side winglets[J].Journal of Mechanical Science and Technology,2013,27(3):703-712.
[10]	Stephens J E,Corke T,Morris S C.Turbine blade tip leakage flow control:thick/thin blade effects and separation line studies[R].ASME Paper GT2008-50705,2008.
[11]	王大磊,邵伏永,郭昊雁,等.翼梢小翼对涡轮间隙泄漏流动影响的数值研究[J].推进技术,2014,35(3):341-346. WANG Dalei,SHAO Fuyong,GUO Haoyan,et al.Study of tip winglets on leakage flow in a transonic turbine stage[J].Journal of Propulsion Technology,2014,35(3):341-346.(in Chinese)
[12]	钟兢军,韩少冰,陆华伟.叶尖小翼对扩压叶栅气动特性影响的数值研究[J].工程热物理学报,2010,31(2):243-246. ZHONG Jingjun,HAN Shaobing,LU Huawei.Numerical simulation of blade tip winglet on the aerodynamic performance of compressor cascade[J].Journal of Engineering Thermophysics,2010,31(2):243-246.(in Chinese)
[13]	韩少冰,钟兢军,严红明.不同长度吸力面小翼对压气机叶栅间隙流场影响的数值研究[J].航空动力学报,2011,26(3):656-661. HAN Shaobing,ZHONG Jingjun,YAN Hongming.Influence of suction-side winglet length on tip leakage flow in compressor cascade[J].Journal of Aerospace Power,2011,26(3):656-661.(in Chinese)
[14]	ZHONG Jingjun,HAN Shaobing,LU Huawei,et al.Effect of tip geometry and tip clearance on the aerodynamic performance of a linear compressor cascade[J].Chinese Journal of Aeronautics,2013:26(3):583-593.
[15]	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 Jingjun,HAN Shaobing.Effects of blended tip winglet on aerodynamic performance of a low speed compressor rotor[J].Journal of Propulsion Technology,2014,35(6):749-757.(in Chinese)
[16]	杨策,马朝臣,王延生,等.透平机械叶尖间隙流场研究的进展[J].力学进展,2011,31(1):70-83. YANG Ce,MA Chaochen,WANG Yansheng,et al.A review of studies on turbomachinery tip gap leakage[J].Advances in Mechanics,2011,31(1):70-83.(in Chinese)
[17]	陈海生,谭春青.叶轮机械内部流动研究进展[J].机械工程学报,2007,43(2):1-12. CHEN Haisheng,TAN Chunqing.Review of investigation into internal flow of turbomachinery[J].Chinese Journal of Mechanical Engineering,2007,43(2):1-12.(in Chinese)
[18]	王雷,刘波,赵鹏程.前掠对高负荷风扇转子叶尖间隙效应的影响[J].航空动力学报,2012,27(8):1841-1847. WANG Lei,LIU Bo,ZHAO Pengcheng.Numerical investigation of effect of forward sweep on tip clearance flows in highly loaded fan rotor[J].Journal of Aerospace Power,2012,27(8):1841-1847.(in Chinese)
[19]	Store J A,Cumpsty N A.Tip leakage flow in axial compressors[J].Journal of Turbomachinery,1991,113(2):252-259.
[20]	Inoue M,Kuronumaru M.Structure of tip clearance flow in an isolated axial compressor rotor[J].Journal of Turbomachinery,1989,111(3):250-256.
[21]	张华良.采用叶片弯/掠及附面层抽吸控制扩压叶栅内涡结构的研究[D].哈尔滨:哈尔滨工业大学,2007. ZHANG Hualiang.Investigation on application of dihedral/swept blade and boundary layer suction to control vortex configurations in compressor cascades[D].Harbin:Harbin Institute of Technology,2007.(in Chinese)
[22]	于贤君.亚音轴流压气机端壁区复杂流动研究及其模化分析[D].北京:北京航空航天大学,2009. YU Xianjun.Experimental investigations and approximate analysis for the three-dimensional flow fields in the endwall region in a subsonic axial compressor stage[D].Beijing:Beijing University of Aeronautics and Astronautics,2009.(in Chinese)
[23]	Kang S.Investigation of the three dimensional flow within a compressor cascade with and without tip clearance[D].Brussel:Vrije Universiteit Brussel,1993.
[24]	Store J A,Cumpsty N A.An approximate analysis and prediction method for tip clearance loss in axial compressors[J].Journal of Turbomachinery,1994,116(4):648-656.
[25]	Khalid S A,Khalsa A S,Waitz I A,et al.Endwall blockage in axial compressors[J].Journal of Turbomachinery,1999,121(3):499-509.
[26]	Bae J W,Breuer K S,Tan C S.Active control of tip clearance flow in axial compressors[J].Journal of Turbomachinery,2005,127(2):352-362.