补燃室长度对固冲发动机二次燃烧的影响  

Influence of afterburning chamber length on secondary combustion for solid ducted rocket motor

作　　者：许超[1] 李进贤[1] 冯喜平[1] 董韬[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《固体火箭技术》2007年第4期292-294,298,共4页Journal of Solid Rocket Technology

基　　金：国家自然科学基金资助项目(50276053)

摘　　要：采用RNGκ-ε湍流模型及单步涡扩散燃烧模型,对二元双下侧进气式固体火箭冲压发动机补燃室内三维反应流场进行了数值模拟,得到了补燃室二次燃烧效率的变化趋势。结合直连式地面模拟试验,分析了补燃室长度对掺混流场和二次燃烧效率的影响。结果表明,增加补燃室长度,可显著提高二次燃烧的效率,但存在一恰当的设计值;大于此设计值时,对提高二次燃烧效率的作用有限。The 3D reaction flow field in the afterburning chamber of solid ducted rocket motor with binary dual-underside inlet mode was numerically simulated by means of RNG K-ε turbulence model and one step eddy-dissipation combustion model. Change trend of combustion efficiency in afterburning chamber was obtained. The influence of afterburning chamber length on secondary combustion efficiency and flow field were analyzed based on direct-connected ground simulation test. The results show that the efficiency of secondary combustion can be improved obviously with increase of afterburning chamber length, but there exists a suitable design value; when the afterburning chamber length is more than the design value, combustion efficiency is improved a little.

关 键 词：固体火箭冲压发动机 补燃室长度 二次燃烧 数值模拟 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]