跨声速压气机转子叶尖非定常流场数值研究

付磊; 宋西镇; 袁巍; 周盛; 陆利蓬

跨声速压气机转子叶尖非定常流场数值研究

北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室, 北京 100191

基金项目: 国家自然科学基金（50906001）

计量
- 文章访问数: 1377
- HTML浏览量: 1
- PDF量: 1001
- 被引次数: 0
出版历程
- 收稿日期: 2013-05-21
- 刊出日期: 2013-12-28

Numerical investigations on unsteady flow field at tip region in transonic compressor rotor

National Key Laboratory of Science and Technology on Aero-Engines Aero-thermodynamics, School of Engergy and Power Engineering, Beijing University of Aeronautics and Astronoucitics, Beijing 100191, China

摘要

摘要: 采用时间精确求解方法对某高负荷跨声速轴流压气机转子在98%设计转速下的叶尖非定常流场进行了数值研究.结果显示，激波自身振荡不明显，叶尖区域流动的非定常性主要来源于叶尖泄漏涡的破碎及其与激波之间的相互干涉.对比设计状态与失速状态下叶尖泄漏涡的特点发现：在近失速点时，叶尖区域间歇性出现前缘溢流.分析表明：叶尖泄漏涡在激波后破碎是造成堵塞的主要原因，也是造成spike型失速初始扰动的原因.
- 跨声速压气机 /
- 非定常流场 /
- 叶尖泄漏涡 /
- 叶尖堵塞 /
- spike型失速
Abstract: Time-accurate simulations were performed to investigate the unsteady flow field at the tip region of a high-loading transonic axial compressor rotor at 98% design rotating speed. The results show that the oscillation of the shock is weak and the unsteadiness at the tip region is originated from the breakdown of tip leakage vortex and the shock/vortex interaction. The characteristics of tip leakage vortex were compared between design condition and near-stall condition. Detailed analysis was then made to emphasize the development of the behavior of tip leakage vortex at near-stall condition, where leading-edge spillage occurred intermittently. The breakdown of the tip leakage vortex after the shock contributes to a large blockage and also the stall disturbance of spike type.
- transonic compressor /
- unsteady flow field /
- tip leakage vortex /
- tip blockage /
- spike stall

HTML

参考文献(16)

[1]	Smith L H.Casing boundary layers in multistage compressors, proceedings of the symposium on flow research on blading[M].Amsterdam, Netherlands:Elsevier Publishing Company, 1970.
[2]	Wisler D C.Loss reduction in axial-flow compressor through low-speed model testing[J].Journal of Turbomachinery, 1985, 107(2):354-363.
[3]	Hah C, Rabe D C, Wadia A R.Role of tip-leakage vortices and passage shock in stall inception in a swept transonic compressor rotor[R].ASME Paper 2004-GT-53867, 2004.
[4]	张靖周, 聂超群, 林峰, 等.叶顶微喷气提高旋转畸变条件下低速轴流压气机失稳裕度的机理分析[J].航空动力学报, 2010, 25(1):67-71. ZHANG Jingzhou, NIE Chaoqun, LIN Feng, et al.Experimental study of the mechanism of improving stall margin of low speed axial-flow compressor with micro-injection under rotating inlet distortion[J].Journal of Aerospace Power, 2010, 25(1):67-71.(in Chinese)
[5]	Nishioka T, Kanno T, Hayami H.Rotating stall inception from spike and rotating instability in a variable pitch axial flow fan.ASME Paper 2008-GT-51466, 2008.
[6]	Furukawa M, Saiki K, Yamada K, et al.Unsteady flow behavior due to breakdown of tip leakage vortex in an axial compressor rotor at near-stall condition[R].ASME Paper 2000-GT-666, 2000.
[7]	Schlechtriem S, Lotzerich M.Breakdown of tip leakage vortices in compressors at flow conditions close to stall[R].ASME Paper 97-GT-41, 1997.
[8]	Adamczyk J J, Celestina M L, Greitzer E M.The role of tip clearance in high-speed fan stall[J].Journal of Turbomachinery, 1993, 115(1):28-39.
[9]	Du J, Lin F, Zhang H W, et al.Numericalinvestigation on the originating mechanism of unsteadiness in tip Leakage flow for a transonic rotor[R].ASME Paper 2008-GT-51363, 2008.
[10]	Suder K L, Celestina M L.Experiment and computational investigation of the tip clearance flow in a transonic axial compressor rotor[R].ASME Paper 94-GT-365, 1994.
[11]	脱伟.处理机匣对跨声速压气机全叶展流场影响的机理探索[D].北京:北京航空航天大学, 2009. TUO Wei.Investigation of the influence of casing treatment on whole span flow field in a transonic compressor[D].Beijing:Beijing University of Aeronautics and Astronautics, 2009.(in Chinese)
[12]	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.
[13]	Leibovich S.The structure of vortex breakdown[J].Annual Review of Fluid Mechanics, 1978, 10(1):221-246.
[14]	Delery J M.Aspects of vortex breakdown[J].Progress in Aerospace Sciences, 1994, 30(1):1-59.
[15]	Vo H D, Tan C S, Greitzer E M.Criteria for spike initiated rotating stall[R].ASME Paper 2005-GT-68374, 2005.
[16]	Khalsa A S, Waitz I A, Tan C S, et al.Endwall blockage in axial compressors[J].Journal of Turbomachinery, 1999, 121(3):499-509.