摘要
在超燃冲压发动机工作过程中,支板前缘的热环境非常恶劣。本文研究了超燃冲压发动机支板前缘的热环境,得到了热载荷分布。提出了支板前缘金属结构再生冷却方案、耐烧蚀材料热防护方案和气体喷射热防护方案,并对这三种方案的热防护效果进行了数值模拟。数值模拟的结果表明,金属结构再生冷却方案无法对支板进行有效的热防护;耐烧蚀材料方案可以在飞行马赫数8以下起到很好的热防护效果;而当马赫数大于8时,则只有气体喷射方案可以实现有效的热防护。
The thermal environment of the scramjet strut leading edge is rigorous. In this paper ,the thermal environment was studied ,and the heat load distribution was obtained. Based on the thermal environment,three thermal protection schemes were put forward,i, e. regeneration cooling scheme ,C/SiC thermal protection scheme and gas jet thermal protection scheme. Numerical simulation was employed to obtain the thermal protection effectiveness of these three schemes. The results show that the regeneration cooling scheme can＇t protect strut leading edge from destruction ;C/SiC thermal protection scheme works well up to flight mach number not exceeding 8,and only gas jet thermal protection scheme can protect strut leading edge from destruction up to Mach 8 and higher.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2006年第2期336-341,共6页
Journal of Aerospace Power
关键词
航空
航天推进系统
超燃冲压发动机
热环境
热防护
aerospace propulsion system
scramjet
thermal environment
thermal protection
