带肋横流通道中气膜孔位置对气膜冷却特性的影响  

Effect of film cooling hole entrance position on film cooling characters in the cross-flow passage with ribs

作　　者：李春林[1] 朱惠人[1] 白江涛[1] 杜小琴[1] 周雷声[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《航空动力学报》2012年第6期1340-1346,共7页Journal of Aerospace Power

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.

关 键 词：气膜冷却 横流通道 肋 相对位置 数值模拟 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]