C/C喉衬热反应边界层内组分分布数值分析  

Numerical analysis of thermal reaction boundary layer species distribution of C/C throat insert

作　　者：李佳明[1] 胡春波[1] 张胜敏[1] 

机构地区：[1]西北工业大学燃烧、热结构与内流场重点实验室,西安710072

出　　处：《固体火箭技术》2012年第2期203-206,共4页Journal of Solid Rocket Technology

基　　金：国家“973”项目(61391)

摘　　要：为研究C/C喉衬热反应边界层内的组分浓度梯度变化规律,基于C/C喉衬的热化学烧蚀理论,建立了组分输运方程。采用有限速率化学反应模型,对C/C喉衬热反应边界层内的组分分布进行了数值研究。计算结果表明,喷管喉部的热化学烧蚀反应最为剧烈,边界层内的热化学烧蚀反应由化学动力学与组分扩散共同控制。推进剂中含铝与否对组分分布影响较大,燃烧室压强及喷管尺寸影响较小。To investigate the concentration of species distributions at thermal chemical boundary layer of C/C throat insert,based on chemical erosion theory for C/C throat insert,species transport equation was established.Numerical study on species distribution inside thermal chemical boundary layer of C/C throat insert was carried out using finite velocity chemical reaction model.The results indicate that erosion is most severe at the nozzle throat,the concentration of the major oxidizing species（affected by the aluminum content of the propellant） exerts a stronger influence on the species distributions than chamber pressure and nozzle size,the kinetics-controlled and diffusion-controlled mechanism occurs at the thermal chemical erosion reactions of the boundary layer.The calculated results show an excellent agreement with the literature results.

关 键 词：C/C喉衬 热反应 边界层 组分分布 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]