具有微小W型肋的结构化表面冲击冷却实验  

Impingement cooling experiment of structured surface with micro-W-shaped ribs

作　　者：陈鹏[1] 饶宇[1] 万超一[1] 

机构地区：[1]上海交通大学机械与动力工程学院叶轮机械研究所,上海200240

出　　处：《航空动力学报》2017年第9期2110-2117,共8页Journal of Aerospace Power

基　　金：国家自然科学基金(51176111)

摘　　要：将冲击冷却技术与肋化表面相结合,研究了一种具有微小W型肋的表面射流冲击冷却结构。通过稳态实验和瞬态热色液晶测试技术来探究光滑靶板和微小W型肋靶板的传热特性。测试时的冲击间距比为1.5,3和5,基于水利直径的雷诺数为15 000~40 000。结果表明:两种靶板的平均努塞尔数和压力损失均随雷诺数的增加而增加,随冲击间距比的增加而减小。当冲击间距比为1.5时,与光滑靶板相比,微小W型肋靶板的平均努塞尔数提高了5.1%~7.3%,压力损失却几乎不变。但当冲击间距比大于3时,由微小W型肋带来的强化传热效果并不显著。The micro-W-shaped ribs roughened plate in a multiple-jet impingement cool-ing system was studied by combining the integrated surface with impingement cooling tech- nology. Steady-state experiments and transient thermal liquid crystal testing technology were used to explore the heat transfer characteristics of multiple-jet impingement onto a flat plate and a roughened plate with micro-W-shaped ribs. The impingement spacing ratios were 1.5, 3 and 5. The Reynolds number based on hydraulic diameter ranged from 15000 to 40000. It was concluded from the results that the averaged Nusselt number and pressure loss increased with the Reynolds number, and decreased with the impingement spacing ratio. Compared with the impingement onto the flat plate, the micro-W-shaped ribs roughened plate can increase the averaged Nusselt number by 5.1% - 7.3 %, when the impingement spacing ratio was i. 5. Howev- er, the increase in pressure loss was negligible. When impingement spacing ratio was larger than 3, the enhancement of heat transfer caused by micro-W-shaped ribs was not distinct.

关 键 词：微小W型肋 冲击冷却 热色液晶(TLC)测试技术 传热 压力损失 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]