Volume 29 Issue 2
Feb.  2014
Turn off MathJax
Article Contents
QIU Ming, ZHOU Zheng-gui, LIU Long-long. Prediction of detached shockwaves from leading edge of supersonic cascade[J]. Journal of Aerospace Power, 2014, 29(2): 363-373. doi: 10.13224/j.cnki.jasp.2014.02.016
Citation: QIU Ming, ZHOU Zheng-gui, LIU Long-long. Prediction of detached shockwaves from leading edge of supersonic cascade[J]. Journal of Aerospace Power, 2014, 29(2): 363-373. doi: 10.13224/j.cnki.jasp.2014.02.016

Prediction of detached shockwaves from leading edge of supersonic cascade

doi: 10.13224/j.cnki.jasp.2014.02.016
  • Received Date: 2013-01-06
  • Publish Date: 2014-02-28
  • In order to accurately predict detached shockwaves from the supersonic cascade leading edge,the supersonic cascade detached shockwaves model based on Moeckel method was built by analysis and formula derivation.Firstly,Moeckel method was improved to increase symmetrical detached shockwaves approximation accuracy on the uniform flow condition.And then,Moeckel method was extended to approximate the asymmetric detached shockwaves on the uniform flow condition.Finally,the detached shockwaves model was constructed according to supersonic cascade flow characteristics.The resulting model was used for three supersonic cascades to predict the shape and position of detached shockwaves from leading edge of cascades.And the predicted results were compared with the CFD solved results.The results show that improved Moeckel method can more accurately approximate symmetrical detached shockwaves and also can be used for predicting asymmetric detached shockwaves,while the shape and location of detached shockwaves obtained by the model is consistent with those obtained by CFD software.

     

  • loading
  • [1]
    Laitone E V,Pardee O O M.Location of detached shock wave in front of a body moving at supersonic speeds[R].NACA RM-A7B10,1947.
    [2]
    郑之初.跨音速下圆球脱体激波[J].空气动力学学报,1984(3):98-103. ZHENG Zhichu.On detached shock wave of sphere moving with transonic velocities[J].Acta Aerodynamica Sinica,1984(3):98-103.(in Chinese)
    [3]
    郑之初,雷晓晓.Ma→1时圆球绕前体流场的数值模拟[J].空气动力学学报,1996,14(1):104-109. ZHENG Zhichu,LEI Xiaoxiao.Computation for flow field about a sphere when Ma→1[J].Acta Aerodynamica Sinica,1996,14(1):104-109.(in Chinese)
    [4]
    Moeckel W E.Approximate method for predicting form and location of detached shock waves ahead of plane or axially symmetric bodies[R].NACA TN-1921,1949.
    [5]
    夏皮罗 A H.可压缩流的动力学与热力学:下册[M].北京:科学出版社,1966.
    [6]
    Klapproth J F.Approximate relative-total-pressure losses of an infinite cascade of supersonic blades with finite leading-edge thickness[R].NACA RM E9L21,1950.
    [7]
    Graham R C,Klapproth J F,Barina F J.Investigation of off-design performance of shock-in-rotor type supersonic blading[R].NACA RM-E51C22,1951.
    [8]
    刘翠娥,吴文权.任意迥转面叶栅超声速进口流场特征线法计算机程序和唯一进气角的确定[J].工程热物理学报,1980,1(3):255-264. LIU Cuie,WU Wenquan.Computer program of supersonic flow past inlet of cascade section on an arbitrary stream filament of revolution and determing unique inlet flow angle[J].Journal of Engineering Thermophysics,1980,1(3):255-264.(in Chinese)
    [9]
    吴仲华,吴文权,华耀南,等.给定激波模型的叶栅跨声流的计算[J].工程热物理学报,1984,5(3):256-261. WU Zhonghua,WU Wenquan,HUA Yaonan,et al.Transonic cascade flow with given shock shapes solved by separate supersonic and subsonic computations[J].Journal of Engineering Thermophysics,1984,5(3):256-261.(in Chinese)
    [10]
    程克明,黄奕裔.跨声速旋成体头部脱体激波的研究[J].南京航空学院学报,1990,22(3):1-6. CHENG Keming,HUANG Yiyi.An investigation on detached shock waves ahead of bodies of revolution at transonic speeds[J].Journal of Nanjing Aeronautical Institute,1990,22(3):1-6.(in Chinese)
    [11]
    阮志坤.平面叶栅栅前激波的改进模型[J].工程热物理学报,1984,5(4):338-341. RUAN Zhikun.An improved model of shock waves in front of two-dimensional cascades[J].Journal of Engineering Thermophysics,1984,5(4):338-341.(in Chinese)
    [12]
    Ladenburg R,Van Voorhis C C,Winckler J.Interferometric study of supersonic phenomena:Part Ⅰ a supersonic air jet at 60 lb/in2 tank pressure [R].Washington:Navy Department Bureau of Ordnance,NAVORD Report 69-46,1946.
    [13]
    Alperin M.A study of detached shock waves in two-dimensions[D].California,US:California Institute of Technology,1950.
    [14]
    Chesnakas C J,Ng W F.Supersonic through-flow fan blade cascade studies[J].Journal of Fluids Engineering,2003,125(5):796-805.
    [15]
    Levine P.Two-dimensional inflow conditions for a supersonic compressor with curved blades[J].Journal of Applied Mechanics,1957,24(2):165-169.
    [16]
    Lichtfuss H J,Starken H.Supersonic cascade flow[J].Progress in Aerospace Science,1974,15:37-149.
    [17]
    York R E,Woodard W S.Supersonic compressor cascades-an analysis of the entrance region flow field contain detached[J].Journal of Engineering for Power,1976,98(2):247-257.
    [18]
    邓向阳.压气机叶顶间隙流的数值模拟研究[D].北京:中国科学院,2006. DENG Xiangyang.Numerical investigation on tip clearance flow in compressor[D].Beijing:Chinese Academy of Sciences,2006.(in Chinese)
    [19]
    韩吉昂.旋转冲压压缩转子进气流道数值仿真及性能研究[D].哈尔滨:哈尔滨工业大学,2009. HAN Ji'ang.Numerical simulation and performance research of flow-path in a Ram-rotor[D].Harbin:Harbin Institute of Technology,2009.(in Chinese)
    [20]
    杜娟.跨音压气机/风扇转子叶顶泄漏流动的非定常机制研究[D].北京:中国科学院,2010. DU Juan.Investigation on the unsteady mechanism of tip leakage flow in transonic compressor/fan rotors[D].Beijing:Chinese Academy of Sciences,2010.(in Chihese)
  • 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

    Article Metrics

    Article views (1602) PDF downloads(1012) Cited by()
    Proportional views
    Related

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return