对转压气机外伸激波对叶顶泄漏流影响

徐强仁; 刘智远; 项效镕; 周小勇; 赵庆军

doi:10.13224/j.cnki.jasp.2019.09.020

对转压气机外伸激波对叶顶泄漏流影响

doi: 10.13224/j.cnki.jasp.2019.09.020

徐强仁^1,2,
刘智远^1,2,
项效镕¹,
周小勇¹,
赵庆军^1,3,2

1.
中国科学院工程热物理研究所,北京 100190
2.
中国科学院大学航空宇航学院,北京 100049
3.
中国科学院工程热物理研究所中国科学院轻型动力重点实验室,北京 100190

基金项目: 国家重点研发计划(2016YFB0901402); 国家自然科学基金(51806215)

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出版历程
- 收稿日期: 2019-01-26
- 刊出日期: 2019-09-28

Impact of bow shock on tip leakage flow in counter-rotating compressor

摘要

摘要: 摘要：为了揭示对转压气机下游转子外伸激波对上游转子泄漏流的影响规律,针对上游转子叶顶间隙分别为0.2、0.5、0.8 mm的对转压气机开展了非定常数值模拟研究。研究发现:受下游转子外伸激波掠扫影响,上游转子尾缘附近压力面会形成弱压缩波,且随上游转子泄漏流增强而逐渐减弱;而该外伸激波在上游转子尾缘附近吸力面,会形成与型线切向相垂直的较强压缩波,且其位置基本不受叶顶间隙大小影响;外伸激波使上游转子尾缘附近吸、压力面压差增大,叶顶泄漏流增强,进而导致其损失增大;随着叶顶间隙增大,上游转子叶尖区弦长前半段压力波动的频率,由通道激波转为叶顶泄漏流主导,且呈现减小的趋势,而弦长后半段压力波动的频率主要由外伸激波主导,且基本不变。
- 外伸激波 /
- 非定常 /
- 高负荷 /
- 叶顶泄漏流 /
- 对转压气机
Abstract: In order to reveal the impact of the bow shock of downstream rotor on the tip leakage flow of upstream rotor in a counter-rotating compressor, the unsteady numerical simulation of a counter-rotating compressor was conducted with tip clearance of 0.2, 0.5 and 0.8 mm of the upstream rotor, respectively. Results showed that impacted by the sweep of the downstream rotor bow shock, a weak compression wave was formed on the pressure surface near the tail edge of the upstream rotor, which could be weakened gradually with the increase of the leakage flow of the upstream rotor. On the suction surface near the trailing edge of the upstream rotor, a strong compression wave perpendicular to the tangential direction of the blade profile was formed causing the downstream rotor bow shock, and its position was basically not affected by the sizes of tip clearance. Also, the pressure difference between the suction and the pressure surfaces near the tail edge of the upstream rotor increased by the bow shock, which led to the augment of the tip leakage flow, and then the flow loss. With the increase of tip clearance, the motivator of the main frequency of the pressure fluctuation, which was located among the blade tip half-chord region belonging to the leading edge of the upstream rotor, was changed from the channel shock to the tip leakage flow and the main frequency decreased gradually. While the blade tip half-chord region was located at the trailing edge, the pressure fluctuation was mainly dominated by the downstream rotor bow shock, and its main frequency was consistent with the bow shock sweeping.
- bow shock /
- unsteady /
- high-load /
- tip leakage flow /
- counter-rotating compressor

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参考文献(32)

[1]	FREEMAN C.Tip clearance effects in axial turbomachines［R］.Belgium:Von Karman Institute Lecture Series,1985.
[2]	DENTON J D.Loss mechanisms in turbomachines［J］.Journal of Turbomachinery,1993,115(4):621-656.
[3]	CUMPSTY N A.Tip leakage flow in axial compressors［J］.Journal of Turbomachinery,1991,113(2):252-259.
[4]	MAILACH R.Experimental investigation of rotating instability in a low-speed research compressor［R］.London:Third European Conference on Turbomachinery-Fluid Dynamics and Thermodynamics,1999.
[5]	MARZ J,HAH C,NEISE W.An experimental and numerical investigation into the mechanisms of rotating instability［R］.ASME Paper GT2001-0536,2001.
[6]	BERGNER J,KINZEL M,SCHIFFER H,et al.Short length-scale rotating inception in a transonic axial compressor-experimental investigation［R］.ASME Paper GT2006-90209,2006.
[7]	HAH C,BERGNER J,SCHIFFER H.Short length-scale rotating stall inception in a transonic axial compressor-criteria and mechanisms［R］.ASME Paper GT2006-90045,2006.
[8]	FURUKAWA M,INOUE M,SAIKI K,et al.The role of tip leakage vortex breakdown in compressor rotor aerodynamics［J］.Journal of Turbomachinery,1999,121(3):469-480.
[9]	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.
[10]	YAMADA K,FURUKAWA M,INOUE M,et al.Unsteady three-dimensional flow phenomena due to breakdown of tip leakage vortex in a transonic axial compressor rotor［R］.ASME Paper GT2004-53745,2004.
[11]	ZHANG H W,DENG X Y,CHEN J Y,et al.Unsteady tip clearance flow in an isolated axial compressor rotor［J］.Journal of Thermal Science,2005,14(3):211-219.
[12]	DU J,LIN F,ZHANG H W,et al.Numerical investigation on the self-induced unsteadiness in tip leakage flow for a transonic fan rotor［J］.Journal of Turbomachinery,2010,132 (2):021017.1-021017.9.
[13]	KNAPKE R D,TURNER M G,LIST M G,et al.Time Accurate simulations of a counter-rotating aspirated compressor［R］.ASME Paper GT2008-50877,2008.
[14]	GUIDOTTI E,TURNER M G.Analysis of the unsteady flow in an aspirated counter-rotating compressor using the nonlinear harmonic method［R］.ASME Paper GT2009-60285,2009.
[15]	高丽敏,苗芳,李瑞宇,等.动/动干涉效应对叶片非定常负荷的影响［J］.航空学报,2014,35(7):1874-1881.GAO Limin,MIAO Fang,LI Ruiyu,et al.Effect of rotor/rotor interactions on blades unsteady loading［J］.Acta Aeronautica et Astronautica Sinica,2014,35(7):1874-1881.(in Chinese)
[16]	王掩刚,陈为雄,陈俊旭.对转压气机叶顶间隙涡非定常数值研究［J］.工程热物理学报,2017,38(1):93-100.WANG Yangang,CHEN Weixiong,CHEN Junxu.Study of transient tip leakage vortex characteristics in a contra-rotating compressor［J］.Journal of Engineering Thermophysics,2017,38(1):93-100.(in Chinese)
[17]	MAO X C,LIU B.Numerical study of the unsteady behaviors and rotating stall inception process in a counter-rotating axial compressor［J］.Journal of Aerospace Engineering,2016,230(14):2716-2727.
[18]	MAO X C,LIU B,ZHAO Hang.Effects of tip clearance size on the unsteady flow behaviors and performance in a counter-rotating axial flow compressor［J］.Journal of Aerospace Engineering,2017,233(3):1059-1070.
[19]	GORRELL S E,THEODORE H,OKIISHI,et al.Stator-rotor interactions in a transonic compressor:Part 1 effect of blade-row spacing on performance［J］.Journal of Turbomachinery,2003,125(2):328-335.
[20]	TURNER M G,GORRELL S E,CAR D.Radial migration of shed vortices in a transonic rotor following a wake generator:a comparison between time accurate and average passage approaches［R］.ASME Paper GT2005-68776,2005.
[21]	GORRELL S E,CAR D,PUTERBAUGH S L,et al.An investigation of wake-shock interactions in a transonic compressor with digital particle image velocimetry and time-accurate computational fluid dynamics［J］.Journal of Turbomachinery,2006,128(4):616-626.
[22]	ESTEVADEORDAL J,GORRELL S,GEBBIE D,et al.PIV study of blade-row interactions in a transonic compressor［R］.AIAA 2007-5017,2007.
[23]	LIST M G,GORRELL S E,TURNER M G.Investigation of loss generation in an embedded transonic fan stage at several gaps using high fidelity,time-accurate CFD［R］.ASME Paper GT2008-51220,2008.
[24]	REYNOLDS S B,GORRELL S E,ESTEVADEORDAL J.PIV analysis on the effect of stator loading on transonic blade-row interactions［R］.ASME Paper GT2010-22576,2010.
[25]	CLARK K P,GORRELL S E.The effects of blade loading on trailing edge vortex formation on a highly loaded stator upstream of a transonic rotor［R］.ASME Paper GT2011-45891,2011.
[26]	CLARK K P,GORRELL S E.Analysis and prediction of shock-induced vortex circulation in transonic compressors［J］.Journal of Turbomachinery,2015,137(12):121007.1-121007.10.
[27]	ESTEVADEORDAL J,GORRELL S,PUTERBAUGH S.PIV measurements of blade-row interactions in a transonic compressor for various operating conditions［R］.AIAA 2008-4700,2008.
[28]	GORRELL S E,CAR D,PUTERBAUGH S L,et al.An investigation of wake-shock interactions in a transonic compressor with digital particle image velocimetry and time-accurate computational fluid dynamics［J］.Journal of Turbomachinery,2005,128(4):616-626.
[29]	GORRELL S E,COPENHAVER W W,CHRISS R M.Effects of upstream wakes on the performance of a transonic compressor stage［R］.Chattanooga,US:Presented at the thirteenth International Symposium on Air Breathing Engines,1997.
[30]	CHRISS R M,COPENHAVER W W,GORRELL S E.The effects of blade-row spacing on the flow capacity of a transonic rotor［R］.ASME Paper 99-GT-209,1999.
[31]	GORRELL S E,COPENHAVER W W,CHRISS R M.Upstream wake influences on the measured performance of a transonic compressor stage［J］.Journal of Propulsion & Power,2001,17(1):43-48.
[32]	YE S B,ZHAO Q J,CUI W W,et al.An improved model for tip clearance loss in transonic axial compressors［J］.Journal of Power and Energy,2018,232(4):295-314.