叶尖间隙对跨声速轴流压气机近失速的影响

谢芳; 楚武利; 李相君; 刘传乐

doi:10.13224/j.cnki.jasp.2014.10.019

叶尖间隙对跨声速轴流压气机近失速的影响

doi: 10.13224/j.cnki.jasp.2014.10.019

1. 西北工业大学动力与能源学院, 西安 710072;
2. 西安高技术研究所机械教研室, 西安 710025;
3. 先进航空发动机协同创新中心, 北京 100191

基金项目:

国家自然科学基金重点项目（51236006）

详细信息

作者简介:
谢芳（1973- ），女，广东东莞人，副教授，博士生，研究领域为叶轮机械气动热力学.

中图分类号: V231.3
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- 被引次数: 0
出版历程
- 收稿日期: 2014-02-23
- 刊出日期: 2014-10-28

Influence of blade tip clearance at near-stall condition on transonic axial-flow compressor

1. School of Power and Energy, Northwestern Polytechnical University, Xi'an 710072;
2. Mechanical Office, Xi'an Institute of High Technology, Xi'an 710025, China;
3. Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China

摘要

摘要: 以跨声速轴流压气机rotor 37为研究对象，利用数值仿真计算方法，采用高密度网格对跨声速轴流压气机设计间隙、1/2设计间隙、1/4设计间隙、2倍设计间隙以及零间隙下近失速状况进行计算.计算结果显示：由设计间隙减小到1/2设计间隙时，跨声速轴流压气机压升和绝热效率损失不大，跨声速轴流压气机失速裕度却提高了4%.在此基础上，引入失速分类方法以及涡动力学理论，对流场进行细节分析.提出适当改变间隙可以有效地拓宽跨声速轴流压气机稳定工作范围，但是间隙改变对泄漏涡破碎以及边界层分离有着重要的影响，甚至诱导不同的失速形式，为跨声速轴流压气机间隙设计提供参考，并且从气动角度探讨在跨声速轴流压气机中应用间隙控制技术的条件.
- 跨声速轴流压气机 /
- 激波 /
- 间隙泄漏流 /
- 边界层分离 /
- 稳定裕度
Abstract: Numerical simulation with high density grid was carried out to study blade tip clearance of a transonic axial-flow compressor rotor 37 at near-stall condition. The blade tip clearance included design clearance, half design clearance, quarter design clearance,2 times design clearance and zero clearance. The results show that stall margin is improved 4%, and adiabatic efficiency and pressure ratio don't decline obviously, when the blade tip clearance reduced from design clearance to half design clearance. Details of the flow field were analyzed based on different stall forms and vortex dynamics. The change of clearance may improve stability margin greatly and clearance plays an important role in leakage vortex and separation of boundary layer, or even induces different stall forms. This has provided necessary basic research for design of the compressor are provided, and discussed the application condition of clearance control technology in aerodynamics.
- transonic axial-flow compressor /
- shock wave /
- clearance leakage flow /
- separation of boundary layer /
- stability margin

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参考文献(18)

[1]	邹正平,李宇,刘火星,等.民用大涵道比涡扇发动机叶轮机某些关键技术[J].航空动力学报,2008,23(8):1504-1518. ZOU Zhengping,LI Yu,LIU Huoxing,et al.Key turbomachinery technology of civil high-bypass-ratio turbofan engine[J].Journal of Aerospace Power,2008,23(8):1504-1518.(in Chinese)
[2]	DeCastro J A,Melcher K M.A study on the requmements for first active turbine tip clearance control[R].AIAA-2004-4176,2004.
[3]	Stinetz B M,Lattime S B,Taylor S,et al.Evaluation of an active clearance control system concept[R].AIAA-2005-3989,2005.
[4]	曾军,王鹏飞.民用航空发动机涡轮叶尖间隙主动控制技术分析[J].航空科学技术,2012,6(2):1-6. ZENG Jun,WANG Pengfei.Analysis on turbine active clearance control technology of civil aircraft engine[J].Aeronautical Science & Technology,2012,6(2):1-6.(in Chinese)
[5]	Smith G D J,Cumpsty N A.Flow phenonmena in compressor casing treament[J].Engineer for Gas Turbines and Power,1984,106(7):532-541.
[6]	Yamada K,Funazaki K,Furukawa M.Behavior of tip clearance flow at near-stall condition in a transonic axial compressor rotor[R].ASME Paper 2007-GT-27725,2007.
[7]	杜鹃,林峰,张宏武,等.跨音速轴流压气机风扇转子叶尖泄漏流的数值研究[J].工程热物理学报,2008,29(12):2027-2032. DU Juan,LIN Feng,ZHANG Hongwu,et al.Numerical simulation on unsteady tip leakage flow in a transonic axial fan rotor[J].Journal of Engineering Thermophysics,2008,29(12):2027-2032.(in Chinese)
[8]	Schlechtriem S,Lotzerich M.Breakdown of tip leakage vortices in compressors at flow conditions close to stall[R].ASME Paper 1997-GT-41,1997.
[9]	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.
[10]	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 strate-gies in axial-flow compressor[D].Xi'an:Northwestern Polytechnical University,2007.(in Chinese)
[11]	谢芳,楚武利,张皓光.跨声速轴流压气机激波/泄漏涡/边界层分离相互作用的影响[J].航空动力学报,2012,27(2):425-430. XIE Fang,CHU Wuli,ZHANG Haoguan.Influence shock waves leakage vortex boundary layer separation interaction in a single-stage transonic axial compressor[J].Journal of Aerospace Power,2012,27(2):425-430.(in Chinese)
[12]	Suder K L,Celestina M L.Experiment and computational investigation of the tip clearance flow in a transonic axial compressor rotor[R].NASA Technical Memorandum 106711,1994.
[13]	Wilke I,Kau H P.A numerical of the influence of casing treatment on the tip leakerage flow in a HPC front stage[R].ASME Paper 2002-GT-30642,2002.
[14]	吴介之,马晖扬,周明德.涡动力引论[M].北京:高等教育出版社,1993.
[15]	童秉纲.非定常流与涡运动[M].北京:国防工业出版社,1993.
[16]	张燕峰.高载荷压气机端壁流动及其控制策略研究[D].西安:西北工业大学,2010. ZHANG Yanfeng.Investigation of endwall flow behaviour and its control strategies in highly loaded compressor[D].Xi'an:Northwestern Polytechnical University,2010.(in Chinese)
[17]	李相君,楚武利,张皓光,等.高负荷跨音速轴流压气机的叶型优化设计[J].计算机仿真,2012,29(7):75-79. LI Xiangjun,CHU Wuli,ZHANG Haoguang,et al.Optimization design for high loading transonic axial compressor blade profile[J].Computer Simulation,2012,29(7):75-79.(in Chinese)
[18]	夏钦斌,王如根,周敏,等.低雷诺数条件下跨声速转子轴向倾斜缝处理机匣扩稳研究[J].航空动力学报,2010,25(6):1389-1393. XIA Qinbin,WANG Rugen,ZHOU Min,et al.Research on the effects of a transonic compressor rotor with axial skewed slots casing treatment at low Reynolds[J].Journal of Aerospace Power,2010,25(6):1389-1393.(in Chinese)