叶尖小翼对跨声速压气机转子变工况性能的影响

韩少冰; 钟兢军

doi:10.13224/j.cnki.jasp.2016.03.016

叶尖小翼对跨声速压气机转子变工况性能的影响

doi: 10.13224/j.cnki.jasp.2016.03.016

大连海事大学轮机工程学院, 辽宁大连 116026

基金项目:

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)

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

辽宁省高校创新团队支持计划(LT2015004)

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研究.

中图分类号: V231.3
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出版历程
- 收稿日期: 2015-09-20
- 刊出日期: 2016-03-28

Influence of blade tip winglet on the off-design performance of a transonic compressor rotor

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

摘要

摘要: 为了进一步揭示叶尖小翼对跨声速压气机转子气动性能的影响机理,利用数值模拟方法研究了不同叶尖小翼安装方式对跨声速压气机转子气动性能的影响,并在分析跨声速压气机转子不同转速时的流动失稳机制的基础上探讨了叶尖小翼的扩稳机理.研究结果表明:最大宽度的压力面小翼在100%,80%及60%设计转速下分别使得跨声速压气机转子失速裕度增加8.1%,17.4%和7.1%.100%及80%设计转速时,转子叶尖区激波/叶尖泄漏涡干涉及泄漏涡破裂后产生的阻塞区是影响跨声速压气机转子内部流动失稳的关键因素.压力面小翼的扩稳机制在于降低了叶尖泄漏流强度,减弱了激波/叶尖泄漏涡干涉的强度,减小了叶尖泄漏涡破裂后产生的阻塞区.60%设计转速时,转子叶片吸力面气动过载导致的大面积的分离流动是诱发该跨声速压气机转子失稳的主要机制,此时压力面小翼的扩稳机制在于降低了转子叶尖来流的等效攻角,减弱了转子吸力面附面层三维分离的程度.
- 叶尖小翼 /
- 跨声速压机转子 /
- 变工况 /
- 激波/叶尖泄漏涡干涉 /
- 旋涡结构
Abstract: In order to further reveal the influence mechanism of blade tip winglet on the aerodynamic performance of transonic compressor rotor, a numerical study of aerodynamic performance of transonic compressor rotor with different blade tip winglets was carried out. Base on the analysis of transonic compressor rotor flow instability at different speeds, the mechanism of stability enhancement by blade tip winglet was discussed. It is found that the stall margin of the transonic compressor rotor with the widest pressure-side winglet can be increased by 8.1%, 17.4% and 7.1% at 100%, 80% and 60% design speed conditions respectively. At 100% and 80% design speed conditions, the shock/tip leakage vortex interaction and the blockage zone caused by the tip leakage vortex breakdown are the key factors inducing the flow instability in a transonic compressor rotor. The mechanism of stability enhancement by pressure-side winglet contributes to the reduction of blockage zone caused by the tip leakage vortex breakdown, due to the strength reduction of tip leakage flow and shock/tip leakage vortex interaction. At 60% design speed condition, the large area boundary separation on the rotor blade suction surface plays an essential role to the flow instability inception. Compared with the rotor without tip winglet, the equivalent incidence of the rotor with pressure-side winglet is reduced and the degree of three-dimensional separation on the suction surface is weakened.
- blade tip winglet /
- transonic compressor rotor /
- off-design /
- shock/tip leakage vortex interaction /
- vortex structure

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参考文献(25)

[1]	Passrucker H,Engber M,Kablitz S,et al.Effect of forward sweep in a transonic compressor rotor[J].Proceedings of the Institution of Mechanical Engineers:Part A Journal of Power and Energy,2003,217(4):357-365.
[2]	Houghton T,Day I.Enhancing the stability of sub-sonic compressors using casing grooves[R].ASME Paper GT2009-59210,2009.
[3]	Cassina G,Beheshti B H,Kammerer A,et al.Parametric study of tip injection in an axial flow compressor stage[R].ASME Paper 2007-GT27403,2007.
[4]	Schuler B J,Kerrebrockn J L,Merchant A.Experimental investigation of a transonic aspirated compressor[J].Journal of Turbomachinery,2005,127(2):340-348.
[5]	Benini E,Biollo R,Ponza R.Efficiency enhancement in transonic compressor rotor blades using synthetic jets:a numerical investigation[J].Applied Energy,2011,88(3):953-962.
[6]	Vo H D,Cameron J D,Morris S C.Control of short length-scale rotating stall inception on a high-speed axial compressor with plasma actuation[R].ASME Paper 2008-GT50967,2008.
[7]	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.
[8]	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.
[9]	Shavalikul A,Camci C.A comparative analysis of pressure side extensions for tip leakage in axial turbines[R].ASME Paper 2008-GT50782,2008.
[10]	Yong C S,Sang W L.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.
[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]	Reid L,Moore R D.Design and overall performance of four highly-loaded,high-speed inlet stages for an advanced high-pressure-ratio core compressor[R].NASA TP-1337,1978.
[17]	Suder K L.Blockage development in a transonic,axial compressor rotor[J].Journal of Turbomachinery,1998,120(3):465-476.
[18]	陈海昕,黄旭东,符松.跨声速压气机机匣处理的数值研究[J].航空动力学报,2007,22(2):298-304. CHEN Haixin,HUANG Xudong,FU Song.CFD study on casing treatment in a transonic compressor[J].Journal of Aerospace Power,2007,22(2):298-304.(in Chinese)
[19]	楚武利,卢新根,吴艳辉.带周向槽机匣处理的压气机内部流动数值模拟与试验[J].航空动力学报,2006,21(1):100-105. CHU Wuli,LU Xingen,WU Yanhui.Numerical and experimental investigations of the flow in a compressor with circumferential grooves[J].Journal of Aerospace Power,2006,21(1):100-105.(in Chinese)
[20]	Beheshti B H,Teixeira J A,Ivey P C.Parametric study of tip clearance-casing treatment on performance and stability of a transonic axial compressor[J].Journal of Turbomachinery,2004,126(4):527-535.
[21]	Legras G,Gourdain N,Trebinjac I.Numerical analysis of the tip leakage flow in a transonic axial compressor with circumferential casing treatment[J].Journal of Thermal Science,2010,19(3):198-205.
[22]	胡加国,王如根,李少伟,等.跨声速轴流压气机径向涡现象与失稳机理[J].航空动力学报,2014,29(9):2239-2246. HU Jiaguo,WANG Rugen,LI Shaowei,et al.Radial vortex phenomenon and instability mechanism of transonic axial-flow compressor[J].Journal of Aerospace Power,2014,29(9):2239-2246.(in Chinese)
[23]	Hunt J C R,Wray A A,Moin P.Eddies,stream,and convergence zones in turbulent flows[R].Center for Turbulence Research Report CTR-S88,1988.
[24]	王如根,胡加国,余超,等.跨声速压气机转子的二次流旋涡结构[J].推进技术,2015,36(4):504-512. WANG Rugen,HU Jiaguo,YU Chao,et al.Research on secondary flow vortex structure in transonic compressor rotor[J].Journal of Propulsion Technology,2015,36(4):504-512.(in Chinese)
[25]	卢新根.轴流压气机内部流动失稳及其被动控制策略研究[D].西安:西北工业大学,2007. LU Xingen.Flow instability and its passive control strategies in axial-flow compressor[D].Xi'an:Northwestern Polytechnical University,2007.(in Chinese)