| SPECIAL TOPIC:HEAT TRANSFER AND THERMAL SYSTEM FOR HEAT TRANSFER AND THERMAL SYSTEM FOR |
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Research progress in transpiration cooling with phase change |
| XU Ruina, LI Xiaoyang, LIAO Zhiyuan, HU Haowei, ZHU Yinhai, JIANG Peixue |
| Key Laboratory for Thermal Science and Power Engineering of Ministry of Education, Department of Energy and Power Engineering, Tsinghua University, Beijing 100084, China |
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Abstract 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 1940s 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.
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| Keywords
thermal protection
transpiration cooling
phase change
self-pumping
optimization
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Issue Date: 11 December 2021
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2021,
Vol. 61
