半封闭肋化通道射流冲击换热特性的数值计算与实验验证  

Numerical Computation and Experimental Examination of Convective Heat Transfer Characteristics of Jet Impingement inside Semi-confined Rib-roughed Channel

作　　者：谭蕾[1] 张靖周[2] 杨卫华[2] 

机构地区：[1]南京航空航天大学航天学院,江苏南京210016 [2]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《航空学报》2008年第5期1105-1111,共7页Acta Aeronautica et Astronautica Sinica

基　　金：航空科学基金(03C52019)

摘　　要：运用数值计算的方法对半封闭肋化通道单排孔射流冲击冷却进行了三维模拟,并采用红外热像测试技术对冲击靶面的温度分布进行了实验研究,揭示出各种流动参数和几何参数对冲击射流传热特性的影响规律。研究结果表明:数值计算与实验特征基本吻合;冲击间距对肋化部分的换热影响较大,在本文研究范围内,Zn/d=1时壁面射流区的换热效果最好;由于产生了两个方向的二次流,V型肋化通道在壁面射流区获得了最佳换热效果。Three-dimensional numerical computation of the flow and heat transfer for jet impingement inside a semi-confined rib-roughed channel was conducted to investigate the effects of flow and geometric parameters on heat transfer characteristics. The temperature distribution on the cooling surface is revealed by a thermograph. The qualitative and quantitative results obtained by both methods are analyzed, which indicate that the present calculation agrees well with experimental data. The coincident results show that impingement cooling effectiveness of a ribbed surface is seriously affected by the jet-to-surface spacing, and the best effect is achieved when the jet-to-surface space is equal to 1. Rib pattern also has great impact on cooling effectiveness. Within the scope of the present research the V-shaped ribs perform best.

关 键 词：冲击冷却 粗糙肋 强化传热 数值计算 热显示 

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] V231.2