航天器高热流射流冷却技术研究综述  

Review on Jet Impingement Technology for Spacecraft High-Heat-Flux Removal

作　　者：朱丽瑶[1] 曹建光[1] 董丽宁[1] 徐涛[1] 

机构地区：[1]上海卫星工程研究所,上海200240

出　　处：《上海航天》2016年第2期106-112,共7页Aerospace Shanghai

基　　金：863重大专项课题(2013AA8073034);星载高热流密度与先进热辐射器技术专项资金资助(51320040101)

摘　　要：基于航天器高热流密度散热的需求,综述了国内外近年单孔和阵列受限式浸没射流技术的研究进展。阐明了射流结构和试验工况等因素对单相/两相换热及流动性能的影响,列出了射流冷却实验研究的条件和结果,分析了换热机理和影响规律。给出了单/多微小通道、冲击表面处理等射流冷却强化结构的研究结果,概括了微通道、肋片和微纳涂层等表面结构对射流冲击换热的原理和强化效果。The experimental and numerical researches on single-phase and two-phase confined impinging jet were reviewed for the requirement of spacecraft high-heat-flux removal in this paper.The effects of jet structure and experiment conditions on heat transfer and flow characteristics were presented.The test results of jet impingement were listed.The heat transfer mechanism and influence law were analyzed.The research results of the different surface structures applied to enhance heat transfer,which were single and multiply microchannel and surface treatment,were discussed. The mechanisms and strengthening effects of the surface structures such as microchannel,fin and micro/nano-coating were also given out.

关 键 词：航天器 高热流密度散热 受限式浸没射流 阵列射流 强化换热 表面结构 微通道 肋片 微纳涂层 

分 类 号：V444.36[航空宇航科学与技术—飞行器设计] TK124[动力工程及工程热物理—工程热物理]