[1] DROST U,BOLCS A.Investigation of detailed film cooling effectiveness and heat transfer distributions on a gas turbine airfoil[J].Journal of Turbomachinery,1999,121(2):233-242.
[2] SEN B,SCHMIDT D L,BOGARD D G.Film cooling with compound angle holes:Heat transfer[J].Journal of Turbomachinery,1996,118(4):800-806.
[3] TENG S,HAN J C,POINSATTE P E.Effect of film-hole shape on turbine-blade heat-transfer coefficient distribution[J].Journal of Thermophysics and Heat Transfer,2001,15(3):249-256.
[4] 戴萍,林枫.气膜孔形状对涡轮叶片气膜冷却效果的影响[J].热能动力工程,2009,24(5):560-565. DAI P,LIN F.Influence of air-film hole shapes on turbine blade air-film cooling effectiveness[J].Journal of Engineering for Thermal Energy and Power,2009,24(5):560-565(in Chinese).
[5] KIM S I,HASSAN I.Unsteady heat transfer analysis of a film cooling flow[C]//46th AIAA Aerospace Sciences Meeting and Exhibit.Reston:AIAA,2008:2008-1287.
[6] OU S,HAN J C,MEHENDALE A B,et al.Unsteady wake over a linear turbine blade cascade with air and CO2 film injection:Part I:Effect on heat transfer coefficients[J].Journal of Turbomachinery,1994,116(4):721-729.
[7] MEHENDALE A B,HAN J C,OU S,et al.Unsteady wake over a linear turbine blade cascade with air and CO2 film injection:Part II:Effect on film effectiveness and heat transfer distributions[J].Journal of Turbomachinery,1994,116(4):730-737.
[8] GAO Z,NARZARY D P,HAN J C.Film cooling on a gas turbine blade pressure side or suction side with axial shaped holes[J].International Journal of Heat and Mass Transfer,2008,51(9):2139-2152.
[9] MHETRAS S,HAN J C.Effect of unsteady wake on full coverage film-cooling effectiveness for a gas turbine blade[C]//Proceedings of 9th AIAA/ASME Joint Thermophysics and Heat Transfer Conference.Reston:AIAA,2006,2:1382-1398.
[10] GOMES R A,NIEHUIS R.Film cooling effectiveness measurements with periodic unsteady inflow on highly loaded blades with main flow separation[J].Journal of Turbomachinery,2011,133(2):021019.
[11] ARDEY S,FOTTNER L.A systematic experimental study on the aerodynamics of leading edge film cooling on a large scale high pressure turbine cascade[C]//Proceedings of the 1998 International Gas Turbine & Aeroengine Congress & Exhibition.Fairfield,NJ:ASME,1998.
[12] MONTOMOLI F,MASSINI M,ADAMI P,et al.Effect of incidence angle with wake passing on a film cooled leading edge:A numerical study[J].International Journal for Numerical Methods in Fluids,2010,63(12):1359-1374.
[13] BENABLED M,AZZI A,JUBRAN B A.Numerical investigation of the influence of incidence angle on asymmetrical turbine blade model showerhead film cooling effectiveness[J].Heat and Mass Transfer,2010,46(8-9):811-819.
[14] MARTELLI F,ADAMI P.Unsteady aerodynamics and heat transfer in transonic turbine stages modelling approaches[C]//8th International Congress of Fluid Dyanmics & Propulsion,2006:14-17.
[15] ADAMI P,MONOTOMOLI F,BELARDINI E,et al.Interaction between wake and film cooling jets:Numerical analysis[C]//Proceedings of the ASME Turbo Expo 2004:Volume 5B:Turbomachinery;Axial Flow Turbine Aerodynamics;Design Methods and CFD Modelling for Turbomachinery;Turbomachines and the Environment.New York:ASME,2004:1053-1063.
[16] 蒋雪辉,赵晓路.非定常尾迹对叶片头部气膜冷却的影响[J].航空动力学报,2005,20(4):540-544. JIANG X H,ZHAO X L.The effect of unsteady wake on leading edge film cooling[J].Journal of Aerospace Power,2005,20(4):540-544(in Chinese).
[17] 谭晓茗,朱兴丹,郭文,等.涡轮叶片前缘气膜冷却换热实验[J].航空动力学报,2014,29(11):2672-2678. TAN X M,ZHU X D,GUO W,et al.Heat transfer experiment on film cooling of turbine blade leading edge[J].Journal of Aerospace Power,2014,29(11):2672-2678(in Chinese).
[18] 张宗卫,朱惠人,刘聪,等.全气膜冷却叶片表面换热系数和冷却效率研究[J].西安交通大学学报,2012,46(7):103-107. ZHANG Z W,ZHU H R,LIU C,et al.Heat transfer coefficient and film cooling effectiveness on a full-film cooling vane[J].Journal of Xi'an Jiaotong University,2012,46(7):103-107(in Chinese).
[19] 周勇,赵晓路,徐建中.非定常激波对气膜冷却影响的数值模拟[J].工程热物理学报,2007,28(6):933-935. ZHOU Y,ZHAO X L,XU J Z.Numerical simulation of the unsteady effect of upstream shocks on film-cooling in a 1+1/2 turbine stage[J].Journal of Engineering Thermophysics,2007,28(6):933-935(in Chinese).
[20] 周莉,张鑫,蔡元虎.非定常尾迹宽度对气膜冷却效果的影响[J].中国电机工程学报,2011,31(29):97-102. ZHOU L,ZHANG X,CAI Y H.Effect of unsteady wake width on the film-cooling effectiveness for a gas turbine blade[J].Proceedings of the CSEE,2011,31(29):97-102(in Chinese).
[21] 周莉,韦威,蔡元虎.非定常尾迹输运对动叶气膜冷却流场影响[J].航空动力学报,2012,27(8):1696-1703. ZHOU L,WEI W,CAI Y H.Effect of unsteady wake transportation on film cooling flowfield of rotating turbine blade[J].Journal of Aerospace Power,2012,27(8):1696-1703(in Chinese).
[22] SCHULTE V,HODSON H P.Unsteady wake-induced boundary layer transition in high lift LP turbines[J].Journal of Turbomachinery,1998,120(1):28-35.
[23] SCHULTE V,HODSON H P.Wake-separation bubble interaction in low pressure turbines:AIAA-1994-2931[R].Reston:AIAA,1994:1-8.
[24] NARZARY D P,GAO Z,MHETRAS S,et al.Effect of unsteady wake on film-cooling effectiveness distribution on a gas turbine blade with compound shaped holes[C]//Proceedings of the ASME Turbo Expo 2007-Power for Land,Sea,and Air.New York:ASME,2007,4 PART A:79-91. |