非壅塞固体火箭冲压发动机二次燃烧室进气方案研究  

Study on secondary combustion chamber air-inlet scheme of unchoked solid rocket ramjet

作　　者：胡建新[1] 夏智勋[1] 王志吉[1] 郭建[1] 张炜[1] 罗振兵[1] 缪万波[1] 

机构地区：[1]国防科技大学航天与材料工程学院,长沙410073

出　　处：《固体火箭技术》2004年第1期28-31,共4页Journal of Solid Rocket Technology

基　　金：武器装备预先研究项目(编号41328020105)。

摘　　要：用k ε湍流模型以及EBU燃烧模型,对固体火箭冲压发动机二次燃烧三维反应流场进行了数值计算,研究了空气射流与富燃燃气射流动量之比、射流速度和燃气发生器喷管数量对二次燃烧的影响。研究结果表明,当空燃动量比在一定范围内时,若空燃动量比变大,则二次燃烧效率升高;降低空气和燃气射流的速度有利于二次燃烧效率的提高;并且增加燃气发生器喷管数量能增强燃气与空气在头部的掺混效果,为燃烧创造良好的条件。Three-dimension reaction flow-field of secondary combustion for solid rocket ramjet is numerically calculated by using k-ε two-equation model and EBU combustion model. The effects of air-fuel momentum ratio, fluidic velocity and gas generator nozzle numbers on secondary combustion is investigated. The results show that increase of air-fuel momentum ratio within proper range and decrease of air-fuel fluidic velocity can improve combustion efficiency, increase of nozzle numbers of gas generator is beneficial to enhance the air-fuel mixing effect in forward region and produce good combustion condition.

关 键 词：非壅塞固体火箭冲压发动机 二次燃烧室 进气方案 数值模拟 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]