中心进气旋转射流冲压燃烧室湍流流动数值模拟  

Numerical simulation on turbulent flow in ramjet chamber with central inlet swirl injection

作　　者：冯喜平[1] 董韬[1] 李进贤[1] 唐金兰[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3期196-200,共5页Journal of Solid Rocket Technology

基　　金：航天科技支撑基金资助项目

摘　　要：采用Reynolds应力方程模型及涡耗散燃烧模型,对头部进气式固体火箭冲压发动机二次燃烧二维轴对称反应流场进行了数值模拟,研究了空气射流和燃气射流无旋、同向旋转和反向旋转3种进气方式对二次燃烧的影响。研究结果表明,当空气射流和燃气射流以有旋状态进入补燃室时,燃料与空气的混合速度变快,化学反应更快,燃烧也更为充分。Tow-dimension axisymmetric reaction flow field of secondary combustion for solid rocket ramjet with head inlet mode was numerically simulated by Reynolds stress equation model and eddy-dissipation combustion model. The effects of three inlet modes on secondary combustion were investigated, i. e. air and fuel injection with non-swirl, co-swirl and counter-swirl mode. The resuhs show that when air and fuel swirl injection enters into secondary chamber, blending rate and chemical reaction become faster, and combustion is finished fully.

关 键 词：固体火箭冲压发动机 旋流进气 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]