铝镁推进剂固冲发动机两相燃烧数值模拟  

Numerical simulation of two-phase combustion for Al/Mg-contained propellant solid rocket ramjet

作　　者：冯喜平[1] 周晓斯[1] 郑亚[1] 李进贤[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》2011年第4期431-435,共5页Journal of Solid Rocket Technology

基　　金：航天科技创新基金重点资助项目

摘　　要：针对铝镁推进剂中心进气固冲发动机,湍流模型采用Reynolds应力方程模型,气相燃烧采用涡耗散模型,两相流采用颗粒随机轨道模型,铝颗粒燃烧采用Brooks燃烧模型,对二次燃烧和流动进行了三维、两相和化学反应流场数值模拟,对比和分析了冲压空气与一次燃气无旋、同向及反向旋转3种工况下补燃室燃烧流动特性及燃烧效率,并对不同工况下的发动机比冲进行了计算分析。研究表明,有旋工况下的铝颗粒燃烧效率均高于无旋工况,采用同向旋转可使补燃室出口总燃烧效率提高约10.02%,颗粒滞留时间可延长约0.699 ms,有旋工况下的发动机比冲均低于无旋工况。Three dimension,two phase and chemical-reaction flow field of secondary combustion and flow for the aluminium-magnesium propellant solid rocket ramjet with central inlet were numerically simulated by Reynolds stress equation model,eddy-dissipation gas combustion model,particle stochastic trajectory model and Brooks aluminium particle combustion model.The characteristics of secondary combustion and flow,as well as the combustion efficiency under three inlet cases were analyzed comparatively,i.e.non-swirl,co-swirl and counter-swirl case.The specific impulses of ramjet under different cases were also calculated.The results show that combustion efficiency of aluminium particle with swirling cases are higher than that the one with no swirling case.The total combustion efficiency of secondary combustion chamber＇s outlet can increase about 10.02% and the residence time of particle can prolong about 0.699 ms in the inlet case of counter-swirl.The specific impulse of ramjet with swirling cases are lower than that the one with no swirling case.

关 键 词：固体火箭冲压发动机 旋转进气 两相燃烧 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]