固冲发动机燃气喷头对燃烧性能的影响研究  

Effects of SDR Gas Injector on Combustion Efficiency

作　　者：何顺强[1,2] 胡凡[1] 刘杰 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073 [2]航天科工集团三十一研究所,北京100074

出　　处：《计算机仿真》2015年第11期97-100,289,共5页Computer Simulation

摘　　要：在固体火箭发动机燃烧性能优化的研究中,由于固体火箭冲压发动机受发射平台的限制,发动机补燃室长径比不到4,仅通过进气方式的调节已经难以实现较高的燃烧效率。根据突扩燃烧在补燃室头部构建回流区,形成局部高温区并延长硼粒子的滞留时间,可促进硼粒子的点火燃烧的研究结果。提出了在不改变补燃室结构尺寸和进气方式的条件下,通过调节燃气喷头结构,增强补燃室头部回流区强度和掺混效果实现发动机燃烧效率提高的方法。同时对比研究了四种燃气喷头对补燃室头部回流区的增加作用,通过数值仿真,对比分析补燃室回流区、温度、硼粒子反应完成度等三个方面。从仿真结果得出,通过优化燃气喷头结构,相同的补燃室结构的燃烧效率提高10%以上,为发动机燃烧性能优化提供了参考。Because of the restriction of launching platforms, the aspect ratio of the secondary combustor of duchted rocket is less than 4. So it is difficult to achieve high combustion efficiency by the way of regulating the intake. According to sudden expansion in the secondary combustion head to build the recirculation zone, a local high temperature is formed and the residence time of the boron particles is extended, which can promote the ignition and combustion of boron particles. In this paper, without changing the size and structure of the secondary combustor, by adjusting the gas injector structure, the strength and the mixing effect of recirculation zone in the head of secondary combustor are increased, and the secondary combustion efficiency is improved. Four types of gas injectors are studied by numerical simulation to analyze the effect on the intensity of recirculation, temperature and the reaction portion of boron particles. The result shows that the designed gas injector can improve combustion efficiency 10% .

关 键 词：固体火箭冲压发动机 燃烧效率 数值分析 

分 类 号：TF765.43[冶金工程—钢铁冶金]