冲击+同向对流+气膜冷却的三维壁温计算与分析  

Numerical computation and analysis of three-dimensional wall temperature of impingement+identical flow convection+film composite cooling

作　　者：王梅娟[1] 宋双文[1] 胡好生[1] 彭剑勇[1] 

机构地区：[1]中国航空工业集团公司中国航空动力机械研究所,湖南株洲412002

出　　处：《航空动力学报》2011年第10期2281-2286,共6页Journal of Aerospace Power

摘　　要：采用Fluent 6.3软件对冲击+同向对流+气膜冷却结构的壁温进行了流固耦合传热计算,获得了该复合冷却结构的壁温和冷却效果分布规律,并将计算结果与试验结果进行了对比.结果表明:冲击+同向对流+气膜冷却具有壁温分布均匀、冷却效果好等优点.计算结果与试验结果的分布趋势一致,最大相对误差为3.6%.Fluid/solid conjugated heat transfer numerical computation was conducted to study impingement＋identical flow convection＋film composite cooling by using Fluent 6.3,and the trend of wall temperature field and the cooling effect were obtained,and then the computational results were compared with the testing results.The results indicate that the wall temperature distribution of the composite cooling is well-proportioned,and the cooling effect is better.The numerical results are in good agreement with the testing results,with their maximal relative error of 3.6%.

关 键 词：火焰筒 冲击冷却 同向对流 气膜冷却 壁温 流固耦合 数值计算 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]