含硼贫氧燃气补燃室反应流场研究  

Numerical simulation of reacting fuel-rich flow field laden with boron particle in the ramjet combustor

作　　者：武渊[1] 田维平[1] 乐发仁[1] 余贞勇[1] 

机构地区：[1]航天科技集团公司第四研究院,陕西西安710025

出　　处：《推进技术》2004年第4期294-297,共4页Journal of Propulsion Technology

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.

关 键 词：固体燃料冲压发动机 硼化物推进剂 二相流 流动分布 

分 类 号：V435.12[航空宇航科学与技术—航空宇航推进理论与工程]