Film cooling characteristics on pressure side of rotating turbine blade

[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 50^th JSASS Conference on Aerospace Propulsion and Power，2010