跨声速轴流压气机近失速状态的间隙泄漏流流动特性

张燕峰; 楚武利; 卢新根

跨声速轴流压气机近失速状态的间隙泄漏流流动特性

西北工业大学动力与能源学院, 西安 710072

基金项目: 航空科学基金(05C53016)

计量
- 文章访问数: 1828
- HTML浏览量: 190
- PDF量: 461
- 被引次数: 0
出版历程
- 收稿日期: 2007-06-25
- 修回日期: 2008-05-05
- 刊出日期: 2008-07-28

Numerical simulation of the flow characteristic of tip leakage flow in a transonic axial-flow compressor at near stall condition

School of Power and Energy, Northwestern Polytechnical University, Xi′an 710072

摘要

摘要: 为了研究间隙泄漏流以及泄漏涡自身的非定常性对轴流压气机的旋转失速的影响.对跨声速轴流压气机NASA转子37进行全三维定常、非定常的数值模拟,对比了最大效率和近失速工况的实验和数值模拟结果,定常计算所获得的总性能与试验结果符合良好.对于非定常计算,详细分析了NASA转子37近失速工况下流场结果,揭示了NASA转子37在近失速工况点,间隙泄漏流存在较明显的非定常性,这种非定常性表现为间隙泄漏流激波干涉引起间隙泄漏涡的周期性破碎.
- 间隙泄漏流 /
- 螺旋型破碎 /
- 非定常流动 /
- 近失速工况
Abstract: Tip clearance flow and the unsteady flow phenomena of tip leakage vortex have great effect to the stall inception of axial-flow compressor.In this paper,3-Dsteady,unsteady numerical simulation of the transonic axial-flow compressor-NASArotor 37 was investigated.Compared to the numerical results and the experimental test case at peak-efficiency and near stall condition,the numerical results agreed well with experimental test data for estimation of the global performance.For the unsteady computation,Detail analyses of the flow field of the NASArotor 37 led to some preliminary conclusion: the tip leakage flow behave obviously unsteady flow phenomena.Shock-vortex induced the periodic breakdown of the tip leakage vortex.
- tip leakage flow /
- spiral-type breakdown /
- unsteady flow /
- near stall condition

HTML

参考文献(10)

[1]	Hoying D A,Tan C S,Vo H D,et al.Role of blade passage flow structures in axial compressor rotating stall inception[J].ASME Journal of Turbomachinery,1999,121(4):735-742.
[2]	Vo H D,Tan C S,Greitzer E M.Criteria for spike initiated rotating stall[R].ASME Paper,2005-GT-68374,2005.
[3]	Hoffman W H,Ballman J.Some aspects of tip vortex behavior in a transonic turbocompressor[R].ISABE Paper,2003-1223,2003.
[4]	Hoffman W H,Ballman J.Flow mechanisms in a transonic turbocompressor at conditions near stall[R].ISABE Paper,2005-1139,2005.
[5]	Yamada K,Furukawa M,lnoue M,et al.Unsteady three-dimensional flow phenomena due to breakdown of tip leakage vortex in a transonic axial compressor rotor[R].ASME Paper,GT2004-53745.
[6]	Bergner J,Kinzel M,Schiffer H,et al.Short length-scale rotating stall inception in a transonic axial compressor-experimental investigation[R].ASME Paper,2006-GT-90209,2006.
[7]	Hah C,Bergner J,Schiffer H.Short length-scale rotating stall inception in a transonic axial compressor-criteria and mechanisms[R].ASME Paper,2006-GT-90045,2006.
[8]	贾希诚,王正明,叶轮机械中间隙流与通道二次流相互作用的数值研究[J].航空动力学报,2002,17(4):439-403.JIA Xicheng,WANG Zhengming.Numerical study of interaction between clearance flow and passage secondary flow in turbomachinery[J].Journal of Aerospace Power 2002,17(4):439-403.(in Chinese)
[9]	聂超群,桂幸民,于清,等.跨音压气机近失速状态的非定常特征,工程热物理学报[J].1999,20(2):171-175.NIE Chaoqun,GUI Xingmin,YU Qing,et al.Unsteady flow behavior of near-stall states in a transonic axial compressor[J].Journal of Engineering Thermophysics,1999,20(2):171-175.(in Chinese)
[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 strategies in axial-flow compressor[D].Xi'an:Northwestern Polytechnical University,2007.(in Chinese)