跨声速压气机转子叶尖非定常流动的数值模拟

卢波; 王志强; 王剑; 高翔

doi:10.13224/j.cnki.jasp.2017.06.026

跨声速压气机转子叶尖非定常流动的数值模拟

doi: 10.13224/j.cnki.jasp.2017.06.026

1.
南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室，南京 210016
2.
中国航空发动机集团有限公司南方工业有限公司，湖南株洲 412002

基金项目: 国家自然科学基金（51406080）；中央高校基本科研业务费专项资金（NJ20150008）

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出版历程
- 收稿日期: 2015-08-27
- 刊出日期: 2017-06-28

Numerical simulation on blade tip unsteady flow in transonic compressor rotor

摘要

摘要: 为了进一步加深对转子叶尖区域非定常流动现象的认识，针对某一跨声速单转子轴流压气机，采用三维非定常数值方法开展了详细研究。对单转子在不同进气条件以及不同工作流量下分别进行非定常模拟，来研究该转子叶尖区域复杂流动结构以及叶尖非定常流动的发展过程。结果表明：不同进气条件下，转子叶尖区域流场结构形式表现不同.当进口非轴向进气时，叶尖非定常流动呈单通道周期形式；而轴向进气时，叶尖区域出现了类似于“旋转不稳定”的沿周向传播的非定常流动现象，且随着工作流量的减小，叶尖区域流场结构也相应发生改变.
- 叶尖泄漏流 /
- 旋转不稳定 /
- 非定常流动 /
- 流场结构 /
- 跨声速压气机
Abstract: The detailed three-dimensional unsteady numerical study was conducted in a transonic compressor rotor to deepen the understanding of unsteady flow phenomenon in rotor blade tip region. Unsteady numerical simulations were studied in single rotor under different inlet conditions and different mass flows, so as to investigate the complex flow structure in rotor blade tip region and the development of blade tip unsteady flow. Results showed that the structure of blade tip flow field varied under different inlet conditions. When inlet direction was non-axial, signal passage periodical form emerged for unsteady flow at blade tip, while an unsteady flow phenomenon like “rotating instability”, spreading along circumferential direction, occurred in blade tip region under axial inlet condition. And with the decrease of mass flow, the structural flow field of blade tip region changed correspondingly.
- blade tip leakage flow /
- rotating instability /
- unsteady flow /
- structure flow field /
- transonic compressor

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参考文献(17)

[1]	BAE J.Active control of tip clearance flow in axial compressors ［D］.Cambridge,Massachusetts:Massachusetts Institute of Technology,2001.
[2]	FURUKAWA M,SAIKI K,NAGAYOSHI K,et al.Effects of stream surface inclination on tip leakage flow fields in compressor rotors［J］.Journal of Turbomachinery,1998,120(4):683-694.
[3]	SCHLECHTRIEM S,LOTZERICH M.Breakdown of tip leakage vortices in compressors at flow conditions close to stall［R］.ASME Paper 97-GT-41,1997.
[4]	JACKSON A D.Stall cell development in an axial compressor［R］.ASME Paper 86-GT-249,1986.
[5]	MEDOUGALL N M,CUMPSTY N A,HYNES T P.Stall inception in axial compressors［R］.ASME Paper 89-GT-63,1989.
[6]	DAY I J,BREUER T,ESCURET J,et al.Stall inception and the prospects for active control in four high-speed compressors［J］.Journal of Turbomachinery,1999,121(1):18-27.
[7]	HOYING D A,TAN C S,VO H D,et al.Role of blade passage flow structures in axial compressor rotating stall inception［J］.Journal of Turbomachinery,1999,121(4):735-742.
[8]	VO H D,TAN C S,GREITZER E M.Criteria for spike initiated rotating stall［J］.Journal of Turbomachinery,2008,130(1):011023.1-011023.9.
[9]	MAILACH R,SAUER H,VOGELER K.The periodical interaction of the tip clearance flow in the blade rows of axial compressors［R］.ASME Paper 2001-GT-0299,2001.
[10]	MAILACH R,LEHMANN I,VOGELER K.Rotating instabilities in an axial compressor originating from the fluctuating blade tip vortex［J］.Journal of Turbomachinery,2001,123(3):453-460.
[11]	MARZ J,HAH C,NEISE W.An experimental and numerical investigation into the mechanisms of rotating instability［R］.ASME Paper 2001-GT-0536,2001.
[12]	KIELB R E,BARTER J W,THOMAS J,et al.Blade excitation by aerodynamic instabilities:a compressor blade study［R］.ASME Paper GT2003-38634,2003.
[13]	付磊,袁巍,宋西镇,等.跨声速压气机转子叶尖流场旋转不稳定现象的数值研究［J］.航空动力学报,2014,24(5):1145-1153.FU Lei,YUAN Wei,SONG Xizhen,et al.Numerical investigation on rotating instability phenomenon in tip flow field of transonic compressor rotor［J］.Journal of Aerospace Power,2014,29(5):1145-1153.(in Chines)
[14]	邓向阳.压气机叶尖间隙流的数值模拟研究［D］.北京：中国科学院,2006.DENG Xiangyang.Numerical investigation on tip clearance flow in compressor［D］.Beijing: Chinese Academy of Sciences,2006.(in Chinese)
[15]	杜娟.跨声速压气机/风扇转子叶尖泄漏流流动的非定常流动机制研究［D］.北京：中国科学院,2010.DU Juan.Investigation on the unsteady mechanism of tip leakage flow in transonic compressor/fan rotors［D］.Beijing: Institute of Engineering Thermophysics,2010.(in Chinese)
[16]	ZHANG Chenkai,HU Jun,WANG Zhiqiang.Investigations on the effects of inflow condition and tip clearance size to the performance of a compressor rotor［J］.Journal of Engineering for Gas Turbines and Power,2014,136(12):122608.1-122608.9.
[17]	WU Yanhui,CHU Wuli.LU Xingen.Behavior of tip-leakage flow in an axial flow compressor rotor［J］.Proceedings of the Institution of Mechanical Engineers:Part A Journal of Power and Energy,2007,221(1):99-110.