涡轮叶栅超声速流场流动特征与气膜冷却特性
Flow field and film cooling characteristics in supersonic turbine cascade
-
摘要: 应用shear strain transport(SST) k-ω 两方程湍流模型,对超声速涡轮叶栅通道内气膜冷却特性进行数值研究,得到不同气膜孔倾角和吹风比下叶栅通道内流场流动特征以及气膜冷却效率的变化规律.在激波入射点附近的气膜射流能够向分离区边界层中补充动量,克服逆压力梯度,有效改善由于激波引起的局部过热.亚声速流动状态下的气膜入射角度对冷却效率的影响能够在较大吹风比下得以体现,而超声速主流状态下,气膜冷却效率与入射角度基本无关,说明亚声速的气膜冷却射流对超声速主流的穿透力要弱于对亚声速主流的穿透力;超声速主流条件下,在激波入射位置的气膜冷却效率要高于激波入射位置下游的气膜冷却效率,这与气膜孔出流在当地的湍流度有关.Abstract: The shear strain transport(SST) k-ω two-equation turbulence model was employed to numerically simulate the film cooling characteristics in the supersonic turbine cascade channel.The flow characteristics in the cascade channel and the change law of the film cooling efficiency were obtained at different gas film hole angles and blow ratios.The film jet near shock incident point can complement momentum to the boundary layer of separation zone,overcome the adverse pressure gradient and effectively improve the local overheating caused by shock wave.In subsonic flow state,the film incidence angle's impact on the efficiency of cooling can be embodied at larger blow ratio;on the contrary,in supersonic flow state,the film cooling efficiency is almost independent of the incidence angle,showing that the penetrating power of subsonic film to the supersonic mainstream is weaker than that to the subsonic mainstream;in the supersonic mainstream state,the film cooling efficiency of the shock incident location is higher than that of the downstream,which is mainly related to local turbulence intensity of the gas film.
-
Key words:
- supersonic turbine cascade /
- supersonic flow /
- film cooling /
- oblique shock /
- numerical simulation
-
[1] Hartnett J P,Birkebak R C,Eckert E R G.Velocity distributions,temperature distributions effectiveness and heat transfer in cooling of a surface with a pressure gradient[J].International Development in Heat Transfer,1961,4,682-689. [2] Carlson L W,Talmor E.Gaseous film cooling at various degrees of hot gas acceleration and turbulence levels[J].Heat Mass Transfer,1968,11(11):1695-1713. [3] Lutum E,Wbifersdoff J,Semmler K,et al.An experimental investigation of film cooling on a convex surface subjected to favorable pressure gradient flow[J].Heat and Mass transfer,2001,44(5):939-951. [4] Lutum E,Wolfersdorf J,Weigand B,et al.Film cooling on a convex surface with zero pressure gradient flow[J].Heat and Mass Transfer,2000,43(6):2973-2987. [5] Lutum E,Wblfersdorf J,Semmler K,et al.Film cooling on a convex surface:influence of external pressure gradient and mach number on film cooling performance[J].Heat and Mass Transfer,2001,38(1):7-16. [6] Aupoix B,Mignosi A,Viala S.Experimental and numerical study of supersonic film cooling[J].AIAA Journal,1998,36(6):915-923. [7] O'Conner J.A numerical study of film cooling in supersonic flow.AIAA 91-4010,1991. [8] Zimmermann H.Calculation of two-and three-dimensional flow in a transonic turbine cascade with particular regard to the losses.AIAA 90-1542,1990. [9] Konopka M,Meinke M,Schroder W.Large-eddy simula tion of supersonic film cooling.AIAA-2010-6792,2010. [10] 彭威,姜培学.直通道和弯曲通道中超声速气膜冷却研究[J].航空动力学报,2008,23(3):406-409. PENG Wei,JIANG Peixue.Supersonic film cooling research in a straight channel and curved channel[J].Journal of Aerospace Power,2008,23(3):406-409.(in Chinese) [11] 彭威,姜培学.变截面主流加速对超声速气膜冷却的影响[J].工程热物理学报,2008,29(2):303-406. PENG Wei,JIANG Peixue.Influence of ariable mainstream acceleration on the supersonic film cooling[J]. Journal of Engineering Thermophysics,2008,29(2):303-406. (in Chinese) [12] Juhany K A,Htmt M L.Flow field measurements in supersonic film cooling including the rffect of shock-wave interaction[J].AIAA Journal,1994,32(3):578-585. [13] Juhany K A,Hunt M L,Sivo J M.Influence of injectant Mach number and temperature on supersonic film cooling[J].Journal of Thermophysics and Heat Transfer,1994,8(1):59-67. [14] Lebedev V P,Lemanov V V,Terekhov V I.Film-cooling emciency in a laval nozzle under conditions of high free stream turbulence[J].Journal of Heat Transfer,2006,128(6):571-579. [15] 王扬平,姜培学.超音速气膜冷却及其受斜激波的影响//中国工程热物理学会传热传质学术年会论文集:下册.北京:中国工程热物理学会,2005:1756-1760. [16] Peng W,Jiang P X.Influence of shock waves on supersonic film cooling[J].Journal of Spacecraft and Rockets,2009,46(1):69-73.
点击查看大图
计量
- 文章访问数: 1358
- HTML浏览量: 4
- PDF量: 971
- 被引次数: 0