航天飞行器热防护相变发汗冷却研究进展  

Research progress in transpiration cooling with phase change

作　　者：胥蕊娜[1] 李晓阳[1] 廖致远 胡皓玮 祝银海[1] 姜培学[1] XU Ruina;LI Xiaoyang;LIAO Zhiyuan;HU Haowei;ZHU Yinhai;JIANG Peixue(Key Laboratoryfor Thermal Scienceand Power Engineeringof Ministryof Education,Department of Energyand Power Engineering,Tsinghua University,Beijing100084,China)

机构地区：[1]清华大学能源与动力工程系,热科学与动力工程教育部重点实验室,北京100084

出　　处：《清华大学学报（自然科学版）》2021年第12期1341-1352,共12页Journal of Tsinghua University(Science and Technology)

基　　金：国家自然科学基金创新研究群体项目(51621062);国家自然科学基金优秀青年基金项目(51722602)。

摘　　要：随着航天飞行器飞行速度与时间的提高,气动、燃烧等带来的超高温、大热流使得飞行器部件温度远超材料耐温极限,高效可靠的热防护技术成为制约航天飞行器发展的重要瓶颈之一。发汗冷却技术自20世纪40年代提出以来,被认为是一种具有极高冷却效率的主动热防护技术,可实现航天飞行器超高温/大热流表面的有效热防护。该文对国际、国内主要研究团队和作者研究团队近年来相变发汗冷却的研究进行了综述,阐述了亚声速和超声速主流中相变发汗冷却流动与换热规律,提出了仿生自抽吸自适应相变发汗冷却方法及其优化结构,给出了发汗冷却在航天飞行器典型热端结构中的应用和优化方法。结合先进材料的发展探索非均匀热流、过载等条件下相变发汗冷却的流动换热规律是未来相变发汗冷却发展的重要方向,从而为航天飞行器跨越式发展提供可靠的技术支持。With the increasing speeds and flight times of aerospace vehicles, the high heat fluxes caused by the aerodynamics and combustion have led to aircraft component temperatures that far exceed the material limits. Efficient, reliable thermal protection methods are then crucial in aerospace components. Transpiration cooling is an efficient active thermal protection method first developed in the 1940 s that is used for thermal protection of conventional materials on ultra-high temperature/heat flux surfaces of aerospace vehicles. This paper reviews international and domestic research including that of the authors’ team on transpiration cooling with phase change in the last several years. The flow and heat transfer mechanisms of transpiration cooling with phase change for subsonic and supersonic mainstream flows are explained. The biomimetic self-pumping and self-adaptive transpiration cooling method and its optimal structures are also presented. This paper also describes the optimization of transpiration cooling in typical thermal structures of aerospace vehicles. Advanced materials will be combined with transpiration cooling with phase change with non-uniform heat fluxes and extremely high temperatures in future designs to provide reliable high speed aerospace vehicles.

关 键 词：热防护 发汗冷却 相变 自抽吸 优化 

分 类 号：TK124[动力工程及工程热物理—工程热物理]