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.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
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)
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
solid ducted rocket motor
afterburning chamber length
secondary combustion
numerical simulation
