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旋转状态下涡轮叶片压力面气膜冷却特性

李国庆 邓宏武 肖俊

李国庆, 邓宏武, 肖俊等 . 旋转状态下涡轮叶片压力面气膜冷却特性[J]. 北京航空航天大学学报, 2010, 36(11): 1286-1289.
引用本文: 李国庆, 邓宏武, 肖俊等 . 旋转状态下涡轮叶片压力面气膜冷却特性[J]. 北京航空航天大学学报, 2010, 36(11): 1286-1289.
Li Guoqing, Deng Hongwu, Xiao Junet al. Film cooling characteristics on pressure side of rotating turbine blade[J]. Journal of Beijing University of Aeronautics and Astronautics, 2010, 36(11): 1286-1289. (in Chinese)
Citation: Li Guoqing, Deng Hongwu, Xiao Junet al. Film cooling characteristics on pressure side of rotating turbine blade[J]. Journal of Beijing University of Aeronautics and Astronautics, 2010, 36(11): 1286-1289. (in Chinese)

旋转状态下涡轮叶片压力面气膜冷却特性

详细信息
    作者简介:

    李国庆(1981-),男,河北灵寿人,博士生,liguoqing@sjp.buaa.edu.cn.

    通讯作者:

    李国庆

  • 中图分类号: V231.1

Film cooling characteristics on pressure side of rotating turbine blade

More Information
    Corresponding author: Li Guoqing
  • 摘要: 通过1.5级涡轮叶片旋转气膜冷却实验,揭示了整级涡轮叶片在旋转状态下的气膜冷却规律.实验中,主流雷诺数为8×104,旋转数分别为2.092,2.324和2.448,吹风比从0.3到3.0变化,冷却工质分别采用空气和二氧化碳,对应射流主流密度比分别为1.03和1.57.叶片表面喷有宽幅液晶,通过高精度CCD相机得到表面温度场.结果表明:压力面上,气膜冷却效率随吹风比的增大而升高,随旋转数的增大而降低;气膜轨迹向高半径方向偏转,偏转程度随旋转数的增大而加剧;提高射流主流密度比,有利于提高冷却效率.

     

  • [1] Goldstein R J.Film cooling[M].New York and London:Advance in Heat Transfer Academic Press,1971,7:321-380 [2] Dring R P,Blair M F,Joslyn H D.An experimental investigation of film cooling on a turbine rotor blade[J].ASME Journal of Engineering for Power,1980,102:81-87 [3] Takeishi K,Aoki S,Sato T,et al.Film cooling on a gas turbine rotor blade[J].Journal of Turbinemachinery,1992,114:828-834 [4] Abhari R S,Epstein A H.An experimental study of film cooling in a rotating transonic turbine[J].Journal of Turbinemachinery,1994,116:63-70 [5] Ahn J,Schobeiri M T,Han J Q,et al.Film cooling effectiveness on the leading edge region of a rotating turbine blade with two rows of film cooling holes using pressure sensitive paint[J].Journal of Heat Transfer,2006,128:879-888 [6] Yang H T,Chen H C,Han J Q,et al.Numerical study of film cooled rotor leading edge with tip clearance in 1-1/2 turbine stage[J].International Journal of Heat and Mass Transfer,2008,51:3066-3081 [7] Garg V K.Adiabatic effectiveness and heat transfer coefficient on a filmcooled rotating blade[J].Numerical Heat Transfer,1997,32(8):811-830 [8] 李国庆,邓宏武,侠晖霞.旋转状态下复合角对气膜冷却效果的影响[J].航空动力学报,2010,25(2):308-313 Li Guoqing,Deng Hongwu,Xia Huixia.Numerical investigation on film cooling effectiveness of rotating blade with multihole[J].Journal of Aerospace Power,2010,25(2):308-313(in Chinese) [9] Li Guoqing,Deng Hongwu,Xiao Jun.Film cooling effectiveness on a rotating turbine[C]//Asian Joint Conference on Propulsion and Power,Miyazaki.Japan:The 50th JSASS Conference on Aerospace Propulsion and Power,2010
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出版历程
  • 收稿日期:  2009-10-23
  • 网络出版日期:  2010-11-30

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