摘要
采用k-ε湍流模型及单步涡扩散化学反应模型,对二次进气结构的固体冲压发动机补燃室的反应流场进行数值模拟,分析了二次进气流量比对燃烧效率与温度场分布的影响。结果表明,在合适流量比下,采用二次进气后补燃室内燃烧效率明显提高,且温度场分布有利于内壁面热防护。
Using k-ε turbulence model and one step eddy-dissipation model, numerical studies on the reacting flow field of solid rocket ramjet with secondary, air inlets were carried out. lnfluence of mass flow ratio on combustion efficiency and temperature field was analyzed. Numerical results show that combustion efficiency increases with a proper mass flow rate ratio, and temperature field is of benefit to thermal protection.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2005年第5期401-403,共3页
Journal of Propulsion Technology
关键词
固体火箭冲压发动机
二次进气
燃烧效率
数值模拟
Solid rocket ramjet
Secondary air inlets
Combustion efficiency
Numerical simulation
