Volume 37 Issue 4
Apr.  2022
Turn off MathJax
Article Contents
Article Navigation >  Journal of Aerospace Power  > 2022  >  37(4): 826-835
LI Ziliang, HAN Ge, ZHU Junqiang, LU Xingen. Mechanism of swept controlling internal flow of transonic centrifugal compressor[J]. Journal of Aerospace Power, 2022, 37(4): 826-835. doi: 10.13224/j.cnki.jasp.20210228
Citation: LI Ziliang, HAN Ge, ZHU Junqiang, LU Xingen. Mechanism of swept controlling internal flow of transonic centrifugal compressor[J]. Journal of Aerospace Power, 2022, 37(4): 826-835. doi: 10.13224/j.cnki.jasp.20210228
shu

Mechanism of swept controlling internal flow of transonic centrifugal compressor

doi: 10.13224/j.cnki.jasp.20210228
  • 1.

    Laboratory of Light-duty Gas-turbine，Institute of Engineering Thermophysics，Chinese Academy of Sciences，Beijing 100190，China

  • 2.

    School of Engineering Science，University of Chinese Academy of Sciences，Beijing 100049，China

  • 3.

    Innovation Academy for Light-duty Gas Turbine，Chinese Academy of Sciences，Beijing 100190，China

  • Received Date: 2021-05-10
  • Publish Date: 2022-04-28
    Abstract
  • Transonic centrifugal compressors face the problem of shock wave controlling.Therefore，the knowledge of the flow mechanism under leading edge swept effect plays an important role in improving the transonic centrifugal compressors performance.Two different transonic centrifugal compressors were investigated by numerical simulations after verified.The results show that,the inducer inlet shock position directly determines the effect of the leading edge swept under the design point.The change of leading edge swept can affect the flow-through capacity by changing the load distribution on the tip of inducer，and furthermore change the shock structure and flow loss on the tip of the inducer.For the impellers whose passage shock wave was swallowed in the blade passages，the backward swept weakened the strength of the passage shock wave and thus reduced the loss near the blade tip of the inducer.However，for the impellers whose leading edge shock wave was detached from leading edge，the forward swept weakened the strength of the leading edge shock wave and made the shock wave more attached，thus reducing the loss near the tip of inducers.

     

    • FullText(HTML)
  • loading
    • References(18)
  • [1]
    KRAIN H.Review of centrifugal compressor's application and development[J].Journal of Turbomachinery，2005,127（1）:25-34.
    [2]
    KANEKO M,TSUJITA H.Numerical investigation of influence of tip leakage flow on secondary flow in transonic centrifugal compressor at design condition[J].Journal of Thermal Science,2015,24（2）:117-122.
    [3]
    DENTON J D,XU L.The exploitation of three-dimensional flow in turbomachinery design[J].Proceedings of the Institution of Mechanical Engineers:Part C Journal of Mechanical Engineering Science,1998,213（2）:125-137.
    [4]
    OKUI H,VERSTRAETE T,BRAEMBUSSCHE R A VAN DEN,et al.Three-dimensional design and optimization of a transonic rotor in axial flow compressors[J].Journal of Turbomachinery,2013,135（3）:031009.1-031009.11.
    [5]
    VAD J.Aerodynamic effects of blade sweep and skew in low-speed axial flow rotors at the design flow rate:an overview[J].Proceedings of the Institution of Mechanical Engineers:Part A Journal of Power and Energy,2008,222（1）:69-85.
    [6]
    HAZBY H,ROBINSON C,CASEY M,et al.Free-form versus ruled inducer design in a transonic centrifugal impeller[J].Journal of Turbomachinery,2018,140（1）:011010.1-011010.12.
    [7]
    ELFERT M,WEBER A,WITTROCK D,et al.Experimental and numerical verification of an optimization of a fast rotating high-performance radial compressor impeller[J].Journal of Turbomachinery,2017,139（10）:101007.1-101007.9.
    [8]
    WITTROCK D,JUNKER M,BEVERSDORFF M,et al.A deep insight into the transonic flow of an advanced centrifugal compressor design[R].ASME Paper GT2019-90308，2019 .
    [9]
    HE Xiao,ZHENG Xinqian.Mechanisms of sweep on the performance of transonic centrifugal compressor impellers[J].Journal of Propulsion and Power，2016，32（5）:1220-1229.
    [10]
    陈思成.跨声速离心压气机的掠叶片设计技术研究[D].北京：北京理工大学,2016.
    [11]
    郭龙凯,刘艳明,郑新前,等.混合型前缘掠对离心压气机气动性能的影响[J].内燃机学报,2016,34（3）:281-287.
    [12]
    RODGERS C.The centrifugal compressor inducer[R].ASME Paper 98-GT-032，1998.
    [13]
    RODGERS C.High specific speed,high inducer tip Mach number,centrifugal compressor[R].ASME Paper GT2003-38949，2003.
    [14]
    PALMER D L,WATERMAN W F.Design and development of an advanced two-stage centrifugal compressor[R].ASME Paper 94-GT-202，1994.
    [15]
    ERDMENGER R R,MICHELASSI V.Impact of main and splitter blade leading edge contour on the performance of high pressure ratio centrifugal compressors[R].ASME Paper GT2014-27062，2014.
    [16]
    GANESH C S,NAGPURWALA Q,DIXIT C.Effect of leading edge sweep on the performance of a centrifugal compressor impeller[J].SASTech-Technical Journal of RUAS,2010,9（2）:55-62.
    [17]
    LI Z,HAN G,LU X,et al.Improving the operating range using a centrifugal compressor with a tandem impeller[EB/OL].[2021-05-05].https:∥www.sciencedirect.com/science/article/pii/S1270963819316165.
    [18]
    ROCHUON N.Analyse de l'écoulement tridimensionnel et instationnaire dans un compresseur centrifuge à fort taux de pression[D].Ecully,France:Ecole Centrale de Lyon,2007.
    • 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(2704.0KB)
    XML

    Article Metrics

    Article views (286) PDF downloads(97) 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