摘要
以King模型模化硼粒子燃烧,以几率密度模型模化湍流燃烧,对含硼贫氧推进剂固体火箭冲压发动机补燃室流场进行数值研究,并与试验结果进行了对比。计算表明:环向燃料喷口布局可增加贫氧燃气气相组分与空气的混合、反应效率;突扩形的几何结构有利于燃气产生大涡运动。
Boron particle combustion model and turbulent no-premixed combustion model were established by using King theory and probability density function in order to study the reacting fuel-rich flow field laden with boron particle in the ramjet combustor. Some obtained numerical results were tested by examination. The results show that dump combustor can produce the large eddy of gas; the ring uniform distribution for fuel injectors can improve the efficiency of reaction and mixing between fuel-rich flow and air.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2004年第4期294-297,共4页
Journal of Propulsion Technology
