摘要
采用数值模拟方法研究了横流通道中气膜孔与肋的相对位置对气膜冷却传热系数和冷却效率的影响.分析了吹风比为0.5,1,2,横流比为0.39,0.585,0.78时孔靠近上游肋、下游肋以及在两肋中间时对冷却效果的影响,研究结果表明:孔位于两肋中间时,气体进入孔时受的冲击较大,外表面传热系数和冷却效率较高;孔靠近上游肋时,气体孔内流动更加均匀,外表面传热系数和冷却效率均较低.
Effect of the relative position between film cooling holes and ribs on the film cooling effectiveness and heat transfer in a channel with cross-flow and ribs was investigated numerically. The effect of position where film cooling holes were close to upstream ribs, downstream ribs and in the middle region of ribs on the cooling effect was studied with blo- wing ratio of 0.5, 1 and 2, with cross-flow ratio of 0.39, 0. 585 and 0.78. The results show that, in the case of the film cooling hole entrance in the middle of two ribs, the flow in the hole are influenced heavily by the entrance jet, the heat transfer coefficient and film cooling effectiveness are higher. In the case of the film cooling hole entrance near the upstream rib, the heat transfer coefficient and film cooling effectiveness are lower.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2012年第6期1340-1346,共7页
Journal of Aerospace Power
关键词
气膜冷却
横流通道
肋
相对位置
数值模拟
film cooling
cross-flow passage
rib
relative position
numerical simulation