单级轴流压气机叶端区二次流动的研究

吴艳辉; 刘军; 安光耀; 陈智洋; 彭文辉

doi:10.13224/j.cnki.jasp.2016.10.010

单级轴流压气机叶端区二次流动的研究

doi: 10.13224/j.cnki.jasp.2016.10.010

1. 西北工业大学动力与能源学院, 西安 71007;
2. 先进航空发动机协同创新中心, 北京 100191

基金项目:

国家自然科学基金（51536006，51276148，11572257）；航空科学基金（2015ZB53027）

详细信息

作者简介:
吴艳辉(1972-),女,新疆霍城人,教授、博士生导师,博士后,主要从事叶轮机械气动热力学研究.

中图分类号: V231.3
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出版历程
- 收稿日期: 2016-03-08
- 刊出日期: 2016-10-28

Investigation of secondary flows near the endwall region in a single-stage axial-flow compressor

1. School of Power and Energy, Northwestern Polytechnical University, Xi'an 71007;
2. Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China

摘要

摘要: 为揭示某单级压气机非设计转速下影响效率和稳定性的关键因素，采用实验和数值模拟相结合的方法，系统地研究了该压气机动、静叶通道内的二次流动随工况（即叶片负荷）的变化规律.对于转子，大流量工况叶端区的二次流主要以泄漏流/泄漏涡和轮毂角区分离为主，而到了峰值效率和近失速工况，整个叶高基元的过度扩压导致的叶片失速抑制了轮毂角区失速的发生.静叶叶尖端区的二次流动虽然具有三维性，但到了近失速工况它依然没有发展成为角区失速.静叶叶根的泄漏流动虽然对端壁附面层的低能流体向轮毂吸力面角区的汇聚起到了一定的抑制作用，但它对角区失速的控制效果却受到压气机不同流量工况的影响.近失速工况叶根泄漏流动抑制角区失速的能力不足是导致压气机效率下降的主要因素，而转子叶尖的二次流动造成的对整个叶尖通道的阻塞是限制压气机稳定性的关键因素.
- 轴流压气机 /
- 叶端区 /
- 二次流动 /
- 泄漏流 /
- 角区失速
Abstract: To determine the key factors influencing the efficiency and stability of a subsonic axial flow compressor stage at off-design speed, experimental and numerical investigations were conducted to analyze the evolution of its secondary flow near the end-wall over a full stable operating range. The results show that a hub corner stall and a tip leakage flow dominate the endwall region of the rotor at a large mass flow condition. However, the full-span blade stall due to the over-diffusion inhibite the hub corner stall at peak efficiency and near stall flow conditions. The flow separation in the corner region of the casing of the stator blade is three-dimensional, but don't evolve into a hub corner stall even at the near stall flow condition. The leakage flow of the stator near hub could decrease and energize the cross-flow due to the overturning of the fluid near the casing, thus inhibiting or mitigating the hub corner stall. However, the control effect is influenced by different flow conditions of the compressor. At the near stall condition, a decrease in the stage efficiency mainly comes from the fact that the leakage flow has not enough capability for suppressing the hub corner stall, while the compressor stage stability is limited by the flow blockage arising from the secondary flow near the rotor tip.
- axial-flow compressor /
- endwall region /
- secondary flows /
- leakage flows /
- corner stall

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参考文献(18)

[1]	Wiseler D C.Loss reduction in axial-flow compressor through low-speed model testing[J].Journal of Engineering for Gas Turbines and Power,1985,107(2):354-363.
[2]	钟兢军,王会社,贾剑波,等.压气机叶栅内二次流的数值研究[J].航空动力学报,2001,16(4):398-401. ZHONG Jingjun,WANG Huishe,JIA Jianbo,et al.Numerical simulation of secondary flow in compressor cascade[J].Journal of Aerospace Power,2001,16(4):398-401.(in Chinese)
[3]	林奇燕,郑群,岳国强.叶栅二次流漩涡结构与损失分析[J].航空动力学报,2007,22(9):1518-1525. LIN Qiyan,ZHENG Qun,YUE Guoqiang.Analysis of secondary flow vortex structure and losses in turbine cascades[J].Journal of Aerospace Power,2007,22(9):1518-1525.(in Chinese)
[4]	Inoue M,Kuroumaru M.Structure of tip clearance flow in an isolated axial compressor rotor[J].Journal of Turbomachinery,1989,111(3):250-256.
[5]	Denton J D.The 1993 IGTI scholar lecture:loss mechanisms in turbomachines[J].Journal of Turbomachinery,1993,115(4):621-656.
[6]	Van Zante D E,Strazisar A J,Wood J R,et al.Recommendations for achieving numerical simulation of tip clearance flows in transonic compressor rotors[J].Journal of Turbomachinery,1999,122(4):733-742.
[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]	Gbadebo S A,Cumpsty N A,Hynes T P.Three-dimensional separations in axial compressors[J].Journal of Turbomachinary,2005,127(4):331-339.
[9]	Dring R P,Joslyn H D,Hardin L W.An investigation of axial compressor rotor aerodynamics[J].Journal of Engineering for Power,1982,104(1):84-96.
[10]	Joslyn H D,Dring R P.Axial compressor stator aerodynamics[J].Journal of Engineering for Gas Turbines and Power,1985,107(2):485-493.
[11]	Schulz H D,Gallus H D.Experimental investigation of the three-dimensional flow in an annular compressor cascade[J].Journal of Turbomachinery,1988,110(4):467-478.
[12]	Schulz H D,Gallus H D,Lakshminarayana B.Three-dimensional separated flow field in the endwall region of an annular compressor cascade in the presence of rotor-stator interaction:Part 1 quasi-steady flow field and comparison with steady-state data[J].Journal of Turbomachinary,1990,112(4):669-678.
[13]	Hah C,Loellbach J.Development of hub corner stall and its influence on the performance of axial compressor blade rows[J].Journal of Turbomachinery,1999,121(1):67-77.
[14]	Weber A,Schreiber H A,Fuchs R,et al.3-D transonic flow in a compressor cascade with shock-induced corner stall[J].Journal of Turbomachinery,2002,124(3):358-366.
[15]	Lei V M,Spakovszky Z S,Greitzer E M.A criterion for axial compressor hub-corner stall[J].Journal of Turbomachinery,2008,130(3):1-10.
[16]	Dong Y,Gallimore S J,Hodson H P.Three-dimensional flows and loss reduction in axial compressors[J].Journal of Turbomachinary,1987,109(3):354-360.
[17]	田江涛,吴艳辉,李清鹏,等.静子轮毂角区失速与间隙流动相互作用机理分析[J].工程热物理学报,2011,32(12):2034-2039. TIAN Jiangtao,WU Yanhui,LI Qingpeng,et al.The analysis of interactional mechanism between hub corner stall and tip leakage flow in an axial-flow compressor stator[J]. Journal of Engineering Thermophysics,2011,32(12):2034-2039. (in Chinese)
[18]	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)