叶尖泄漏流对压气机稳定性影响的数值分析

王昊; 屠宝锋

doi:10.13224/j.cnki.jasp.2021.02.010

叶尖泄漏流对压气机稳定性影响的数值分析

doi: 10.13224/j.cnki.jasp.2021.02.010

王昊,
屠宝锋

基金项目: 国家科技重大专项（2017-Ⅱ-0004-0017）

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出版历程
- 收稿日期: 2020-06-23
- 刊出日期: 2021-02-28

Numerical analysis of tip leakage flow effect on compressor stability

College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China

摘要

摘要: 为研究叶尖泄漏流对稳定性的影响,发展了一种叶尖泄漏涡模型,并且在由课题组开发的TUSIAC(three dimensional and unsteady stall inception analysis code)程序中实现。该程序将转/静子叶排模化为三维激盘,并在无叶区求解三维非定常欧拉方程,黏性的影响通过特性曲线体现,因此对计算资源的要求较低。数值模拟的结果表明：在叶尖间隙的影响下,压气机的性能和稳定裕度均有所下降。叶尖间隙不改变失速先兆的类型,但使得失速团旋转速度加快,周向尺寸减小。所发展的叶尖涡模型能够预测叶尖间隙尺寸对压气机稳定边界与失速起始过程的影响,从而为在设计初期考虑压气机的气动稳定性、并且优化压气机设计,提供了一种较为实用的方法。
- 压气机稳定性 /
- 叶尖泄漏流 /
- 激盘模型 /
- 计算流体力学 /
- 旋转失速
Abstract: To study the effect of tip leakage flow on the compressor stability, a tip leakage vortex model was developed, and implemented in the TUSIAC (three dimensional and unsteady stall inception analysis code) program. The program modeled rotors/stators as three dimensional actuator disks, where the viscous effect was reflected by the characteristic curve, and the three-dimensional unsteady Euler equations in the flow passages between them were solved, thus lower computational resources were required. The numerical simulation showed that the performance and stable margin of the compressor were degraded under the effect of tip clearance.The tip clearance did not change the type of the stall precursor, but shrinked the circumferential size of the stall cell, and made it rotate faster.The newly developed tip vortex model could predict the tip clearance effect on the compressor stability and the stall inception process, thus providing a practical approach to investigate the compressor stability and optimize the compressor design during the preliminary design phase.
- compressor stability /
- tip leakage flow /
- actuator disk model /
- computational fluid dynamics /
- rotating stall

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参考文献(19)

[1]	EMMONS H L,PEARSON C E,GRANT H P.Compressor surge and stall propagation［R］.ASME Paper GT2017-64066,2017.
[2]	FREEMAN C.Effect of tip clearance on compressor stability and engine performance［R］.von Karman Institute for Fluid Dynamics Lecture Series 1985-05,1985.
[3]	DAY I J.Stall inception in axial flow compressors［J］.Journal of Turbomachinery,1993,115(1):1-9.
[4]	CAMP T R,DAY I J.A Study of spike and modal stall phenomena in a low-speed axial compressor［J］.Journal of Turbomachinery,1998,120(3):393-401.
[5]	VO H D,TAN C S,GREITZER E M.Criteria for spike initiated rotating stall［J］.Journal of Turbomachinery,2008,130(1):155-165.
[6]	TAN C S.Three-dimensional and tip clearance flows in compressors［R］.von Karman Institute for Fluid Dynamics Lecture Series 2006-06,2006.
[7]	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.
[8]	SCHLECHTRIEM S,LTZERICH M.Breakdown of tip leakage vortices in compressors at flow conditions close to stall［R］.ASME Paper 97-GT-041,1997.
[9]	FURUKAWA M,INOUE M,SAIKI K,et al.The role of tip leakage vortex breakdown in compressor rotor aerodynamics［R］.ASME Paper 98-GT-239,1998.
[10]	ZHANG C,HU J,WANG Z,et al.Numerical study on tip leakage flow structure of an axial flow compressor rotor［R］.ASME Paper GT2014-27291,2014.
[11]	VANZANTE D E,STRAZISAR A J,WOODJ R,et al.Recommendations for achieving accurate numerical simulation of tip clearance flows in transonic compressor rotors［J］.Journal of Turbomachinery,2000,122(4):733-742.
[12]	YOU D,WANG M,MOIN P,et al.Large-eddy simulation analysis of mechanisms for viscous losses in a turbomachinery tip-clearance flow［J］.Journal of Fluid Mechanics,2007,586:177-204.
[13]	INOUE M,FURUKAWA M,SAIKI K,et al.Physical explanations of tip leakage flow fields in an axial compressor rotor［R］.ASME Paper 98-GT-91,1998.
[14]	屠宝锋.风扇/压气机动态失速过程和多尺度非定常气动稳定性研究［D］.南京:南京航空航天大学,2012. TU Baofeng.Dynamic stall inception and multi-scale unsteady aerodynamic stability investigation of fan/compressor［D］.Nanjing:Nanjing University of Aeronautics and Astronautics,2012.(in Chinese)
[15]	MARTINEZ-SANCHEZ M,GAUTHIER R P.Blade scale effects of tip leakage［R］.Gas Turbine Laboratory，Massachusetts Institute of Technology,GTL-202GT & PDL report No.202,1990.
[16]	CHEN G T.Vortical structures in turbomachinery tip clearance flows［D］.Boston,US:Masachusetts Institute of Technology,1991.
[17]	SONG S J,MARTINEZ-SANCHEZ M.Rotordynamic forces due to turbine tip leakage:Part Ⅰ blade scale effects［J］.Journal of Turbomachinery,1997,119(4):695-703.
[18]	MARTINEZ-SANCHEZ M.Rotordynamic forces due to turbine tip leakage:Part Ⅱ radius scale effects and experimental verification［J］.Journal of Turbomachinery,1997,119(4):704-713.
[19]	SONG S J,CHO S H.Nonuniform flow in a compressor due to asymmetric tip clearance［J］.Journal of Turbomachinery,2000,122(4):751-760.