留言板

尊敬的读者、作者、审稿人, 关于本刊的投稿、审稿、编辑和出版的任何问题, 您可以本页添加留言。我们将尽快给您答复。谢谢您的支持!

姓名
邮箱
手机号码
标题
留言内容
验证码

超声叶栅前缘处的脱体激波预测

邱名 周正贵 刘龙龙

邱名, 周正贵, 刘龙龙. 超声叶栅前缘处的脱体激波预测[J]. 航空动力学报, 2014, 29(2): 363-373. doi: 10.13224/j.cnki.jasp.2014.02.016
引用本文: 邱名, 周正贵, 刘龙龙. 超声叶栅前缘处的脱体激波预测[J]. 航空动力学报, 2014, 29(2): 363-373. doi: 10.13224/j.cnki.jasp.2014.02.016
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

超声叶栅前缘处的脱体激波预测

doi: 10.13224/j.cnki.jasp.2014.02.016

Prediction of detached shockwaves from leading edge of supersonic cascade

  • 摘要: 为了准确预测超声叶栅前缘处的脱体激波,以Moeckel法为基础,通过分析和公式推导,构造叶栅前缘处的脱体激波模型.首先对Moeckel法进行改进,提高均匀来流条件下的对称脱体激波逼近精度;然后再将Moeckel法推广到均匀来流条件下的非对称脱体激波逼近;最后结合超声叶栅流动特征,给出叶栅前缘处的脱体激波模型.将所得模型用于3个超声叶栅,预测叶栅前缘处的脱体激波形状和位置,并将预测结果与CFD软件求解结果进行比较.结果表明:在均匀来流条件下,改进后的Moeckel法能更准确地逼近对称脱体激波,并可用于逼近非对称脱体激波;由超声叶栅脱体激波模型确定的脱体激波形状和位置与CFD求解结果一致性很好.

     

  • [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
计量
  • 文章访问数:  1327
  • HTML浏览量:  2
  • PDF量:  1009
  • 被引次数: 0
出版历程
  • 收稿日期:  2013-01-06
  • 刊出日期:  2014-02-28

目录

    /

    返回文章
    返回