高超声速气膜冷却技术研究进展及发展方向

Research Progress and Development Direction of Hypersonic Film Cooling Technology

随着飞行器速度的进一步提高以及对可重复使用飞行器的需求,高超声速气膜冷却技术已经成为航空航天技术发展的热点问题。开展高超声速飞行器主动气膜冷却技术研究,对于解决高超声速飞行器面临的热防护问题,突破防热技术瓶颈,有十分重要的意义。本文在对主动冷却热防护技术原理、分类及其机制进行系统研究的基础上,从实验研究和数值模拟两个维度,对二维槽缝气膜孔工艺、离散气膜孔工艺和高超声速逆向喷流技术等高超声速气膜冷却技术以及影响气膜冷却效果的因素的研究现状进行了梳理和分析,进而提出了高超声速气膜冷却技术的防热材料研制、材料制备工艺、多气膜孔特性实验研究、逆向喷流气膜孔冷却技术实验验证等研究方向。

With the further increasement of vehicle speed and the demand for reusable vehicles,hypersonic film cooling technology has become a hot issue in the development of aerospace technology.The research on active film cooling technology of hypersonic vehicle is very important to solve the problem of thermal protection and break through the bottleneck of thermal protection technology.In this paper,the principle,classification and mechanism of active cooling thermal protection technology are studied firstly.Then,from both experimental research and numerical simulation point of view,the research status of two-dimensional slot film cooling technology,discrete film hole technology and hypersonic reverse jet technology,as well as the factors affecting the film cooling effect are reviewed and analyzed.At last,the research directions such as heat-resistant material development,material preparation process,experimental study of multi film hole characteristics,experimental verification of reverse jet film hole cooling technology for hypersonic film cooling technology are put forward.