Volume 34 Issue 12
Dec.  2019
Turn off MathJax
Article Contents
Article Navigation >  Journal of Aerospace Power  > 2019  >  34(12): 2706-2718
CHEN Zhiyang, WU Yanhui, AN Jinhuaiyuan. Impact of Reynolds number on unsteady flow in axial flow compressor rotor[J]. Journal of Aerospace Power, 2019, 34(12): 2706-2718. doi: 10.13224/j.cnki.jasp.2019.12.020
Citation: CHEN Zhiyang, WU Yanhui, AN Jinhuaiyuan. Impact of Reynolds number on unsteady flow in axial flow compressor rotor[J]. Journal of Aerospace Power, 2019, 34(12): 2706-2718. doi: 10.13224/j.cnki.jasp.2019.12.020
shu

Impact of Reynolds number on unsteady flow in axial flow compressor rotor

doi: 10.13224/j.cnki.jasp.2019.12.020

  • Shaanxi Key Laboratory of Internal Aerodynamics in Aero-Engine,School of Power and Energy,Northwestern Polytechnical University,Xi’an 710072,China

  • Received Date: 2019-06-10
  • Publish Date: 2019-12-28
    Abstract
  • Experimental measurements were conducted for an axial high-speed subsonic compressor rotor on the ground. Numerical investigations were carried out at two altitudes to explore the mechanism of circumferential propagation characteristic at different Reynolds number (Re). Results showed that, on the ground, rotating instability (RI) was measured near stall condition, which was characterized by a hump frequency band in the spectrum. Characteristic frequencies of numerical pressure signals were limited in the frequency band of RI on the ground. The spectrums of the neighboring passages indicated that the flow unsteadiness rotated in the compressor. The circumferential disturbance was result of the periodic interaction between the blade tip leakage flow and the blade tip load. At the altitude of 20 km, there were several circumferential disturbances with different characteristic frequencies in the compressor near stall condition. The radial flow from the hub to tip induced by the suction surface flow separation was dominant in the tip region. The blade tip load was influenced both by the radial flow and tip leakage flow, as a result of the circumferential disturbance at low Re.

     

    • FullText(HTML)
  • loading
    • References(34)
  • [1]
    MCDOUGALL N M,CUMPSTY N A,HYNEST P.Stall inception in axial compressors［J］.Journal of Turbomachinery,1990,112(1):116-123.
    [2]
    GARNIER V H,EPSTEIN A H,GREITZER E M.Rotating waves as a stall inception indication in axial compressors［J］.Journal of Turbomachinery,1991,113(2):290-301.
    [3]
    DAY I J.Stall inception in axial flow compressors［J］.Journal of Turbomachinery,1993,115(1):1-9.
    [4]
    MRZ J,HAH C,NEISE W.An experimental and numerical investigation into the mechanisms of rotating instability［J］.Journal of Turbomachinery,2002,124(3):367-374.
    [5]
    WU Yanhui,WU Junfeng,ZHANG Gaoguang,et al.Experimental and numerical investigation of flow characteristics near casing in an axial flow compressor rotor at stable and stall inception conditions［J］.Journal of Fluids Engineering,2014,136(11):1491-1503.
    [6]
    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):453-463.
    [7]
    YAMADA K,KIKUTA H,FURUKAWA M,et al.Effects of tip clearance on the stall inception process in an axial compressor rotor［R］.ASME Paper GT2013-95479,2013.
    [8]
    BIELA C,MULLER M W,SCHIFFER H.Unsteady pressure measurement in a single stage axial transonic compressor near the stability limit［R］.ASME Paper GT2008-50245,2008.
    [9]
    ZHANG H W,DENG X Y,LIN F,et al.Unsteady tip leakage flow in an isolated axial compressor rotor［J］.Journal of Thermal Science,2005,143,211-219.
    [10]
    TONG Z T,LIN F,CHEN J Y,et al.The Self-Induced unsteadiness of tip leakage vortex and its effect on compressor stall inception［R］.ASME Paper GT2007-27010,2007.
    [11]
    DU Juan,LIN Feng,ZHANG Hongwu,et al.Numerical investigation on the originating mechanism of unsteadiness in tip leakage flow for a transonic fan rotor［R］.ASME Paper GT2008-51463,2008.
    [12]
    DU Juan,LIN Feng,CHEN Jingyi,et al.Flow structures in the tip region for a transonic compressor rotor［J］.Journal of Turbomachinery,2013,135(3):031012.1-031012.11.
    [13]
    MAILACH R,SAUER H,VOGELER K.The periodical interaction of the tip clearance flow in the blade rows of axial compressors［R］.ASME Paper GT2001-0299,2001.
    [14]
    王昊,吴亚东,欧阳华.低速轴流压气机中气动旋转不稳定性和叶顶泄漏流脉动特性［J］.航空动力学报,2016,31(9):2239-2250. WANG Hao,WU Yadong,OUYANG Hua.Aerodynamic rotating instability and fluctuated characteristics of tip clearance flow in low speed axial flow compressor［J］.Journal of Aerospace Power,2016,31(9):2239-2250.(in Chinese)
    [15]
    王昊,吴亚东,欧阳华.压气机叶顶泄漏流振荡周向传播特性的数值模拟［J］.航空动力学报,2017,32(3):538-548. WANG Hao,WU Yadong,OUYANG Hua.Numerical simulations on circumferential propagating characteristics of tip leakage flow oscillation in compressor［J］.Journal of Aerospace Power,2017,32(3):538-548.(in Chinese)
    [16]
    HAH C,BERGNER J,SCHIFFER H.Tip clearance vortex oscillation,vortex shedding and rotating instabilities in an axial transonic compressor rotor［R］.ASME Paper GT2008-50105,2008.
    [17]
    HAH C,VOGES M,MUELLER M,et al.Characteristics of tip clearance flow instability in a transonic compressor［R］.ASME Paper GT2010-22101,2010.
    [18]
    WU Yanhui,WU Junfeng,ZHANG Gaoguang,et al.Experimental and numerical investigation of flow characteristics near casing in an axial flow compressor rotor at stable and stall inception conditions［J］.Journal of Fluids Engineering,2014,136(11):111106.1-111106.14.
    [19]
    吴艳辉,丁永鹏,安光耀,等.跨声速压气机转子叶尖区涡系结构分析［J］.工程热物理学报,2016,37(9):1838-1845. WU Yanhui,DING Yongpeng,AN Guangyao,et al.Investigation of vortex structure near tip region in a transonic axial flow compressor rotor［J］.Journal of Engineering Thermophysics,2016,37(9):1838-1845.(in Chinese).
    [20]
    吴艳辉,安光耀,陈智洋,等.跨声速压气机转子近失速工况非定常流动及相关机理研究［J］.推进技术,2016,37(9):1847-1854. WU Yanhui,AN Guangyao,CHEN Zhiyang,et al.Numerical investigation into unsteady flow and its associated flow mechanism in a transonic compressor rotor at near stall conditions［J］.Journal of Propulsion Technology,2016,37(9):1847-1854.(in Chinese)
    [21]
    VO D H.Role of tip clearance flow in rotating instabilities and nonsynchronous vibrations［J］.Journal of Propulsion and Power,2010,26(3):556-561.
    [22]
    KAMEIER F,NEISE W.Rotating blade flow instability as a source of noise in axial turbomachines［J］.Journal of Sound and Vibration,1997,203(5):833-853.
    [23]
    LIU J M,HOLSTE F,NEISE W.On the azimuthal mode structure of rotating blade flow instabilities in axial turbomachines［R］.AIAA 96-1741,1996.
    [24]
    BAUMGARTNER M,KAMEIER F,HOURMOUZIADIS J.Non-engine order blade vibration in a high pressure compressor［R］.Melbourne,Australia:the 12th International Symposium on Airbreathing Engines,1995.
    [25]
    CHEN Zhiyang,WU Yanhui,AN Guangyao,et al.Investigation into flow mechanism leading to the step change in aerodynamic modes of rotating instabilities in a subsonic axial compressor rotor［R］.ASME Paper GT2017-63286,2017.
    [26]
    NISHIOKA T,KURODA S,NAGANO T,et al.Influence of rotating instability on stall inception patterns in a variable-oitch axial-flow fan［R］.ASME Paper GT2006-90589,2006.
    [27]
    NISHIOKA T,KANNO T,HIRADATE K.Rotor-tip flow fields near inception point of rotating instability in an axial-flow fan［R］.ASME Paper GT2011-45338,2011.
    [28]
    卢新根.轴流压气机内部流动失稳及其被动控制研究［D］.西安:西北工业大学,2007. LU Xingen.Flow Instability and Its Passive Control Strategies in an Axial Flow Compressor［D］.Xi’an:Northwest Polytechnic University,2007.(in Chinese)
    [29]
    WU Yanhui,CHEN Zhiyang,AN Guangyao,et al.Origins and structure of rotating instability:Part 1 experimental and numerical observations in a subsonic axial compressor rotor［R］.ASME Paper GT2016-56221,2016.
    [30]
    陈智洋,吴艳辉,安光耀,等.轴流压气机转子旋转不稳定性检测及机理探讨［J］.推进技术,2017,38(11):2401-2410. CHEN Zhiyang,WU Yanhui,AN Guangyao,et al.Experimental detection of rotating instability and exploration of its flow mechanism in an axial flow compressor rotor［J］.Journal of Propulsion Technology,2017,38(11):2401-2410.(in Chinese)
    [31]
    CHEN Zhiyang,WU Yanhui,AN Guangyao,et al.Investigation into the flow mechanism of rotating instabilities in a subsonic Axial compressor rotor［J］.Fluid Dynamic Research,2018,50(6):065509.1-065509.19.
    [32]
    王如根,周敏,赵英武,等.跨声速压气机低雷诺数下流动失稳机制研究［J］.航空动力学报,2009,24(2):414-419. WANG Rugen,ZHOU Min,ZHAO Yingwu,et al.Research on flow instability mechanism of transonic compressor at low Reynolds number［J］.Journal of Aerospace Power,2009,24(2):414-419.(in Chinese)
    [33]
    周敏,王如根,白云,等.低雷诺数下跨声速压气机转子失速工况时流动失稳触发过程研究［J］.航空动力学报,2009,24(6) 1379-1384. ZHOU Min,WANG Rugen,BAI Yun,et al.Research on flow instability triggering process at stall condition of transonic compressor rotor at low Reynolds number［J］.Journal of Aerospace Power,2009,24(6):1379-1384.(in Chinese)
    [34]
    杨琳,邹正平,宁方飞,等.边界层转捩的数值模拟［J］.航空动力学报,2005,20(3):355-360. YANG Lin,ZOU Zhengping,NING Fangfei,et al.Simulation of boundary layer transition［J］.Journal of Aerospace Power,2005,20(3):355-360.(in Chinese)
    • Relative Articles
    • Supplements(0)
    • Cited By
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索
    Get Citation
    PDF(1076.0KB)
    XML

    Article Metrics

    Article views (662) PDF downloads(331) Cited by()
    Proportional views
    Related

    Copyright © 《Journal of Aerospace Power》 All Rights Reserved.

    Supported by: Beijing Renhe Information Technology Co., Ltd.  

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return