摘要
在Mg/CO2粉末火箭发动机的研究中,镁颗粒的燃速、颗粒粒径以及颗粒喷注速度是影响金属粉末燃烧特性的主要因素,金属粉末的燃烧特性决定了燃烧室的结构参数。采用RNG k-ε方程和层流有限速率化学反应模型对轴向喷注式圆柱型燃烧室燃烧性能进行了三维定常数值仿真,研究了颗粒粒径及喷注速度对燃烧室中反应特性的影响,旨在为发动机结构尺寸确定提供参考,所建立计算模型与实际参数吻合较好。仿真结果表明:小粒径镁粉燃烧比较充分,颗粒粒径过大导致燃烧效率低下;镁粉燃烧放热峰随喷注速度的增加而向燃烧室后端移动,喷注速度过大则导致燃烧不完全;金属颗粒径向扩散很少,导致燃烧室壁面附近化学反应量较少且温度较低,可以利用来增强热防护能力。
In Mg/CO2 powdered rocket motor, the combustion character of metal powder determines the structural parameters of combustor. Burning rate, particle diameter and injection velocity of magnesium powder are the main factors those combustion characters can effect the metal powder. Three - dimensional steady numerical simulation was carried out by means of k - e equation of RNG model and laminar finite - rate model to research the combustion per- formance of cylindrical axial injection combustor. The research about diameter and injection velocity of particle effec- ting combustion character was proceeded in order to provide reference for combustor size determining. The computa- tion model established can fit the actual argument well. The result shows that magnesium powder with smaller size combusts more completely, on the contrary, larger size powder results in low combustion efficiency. Exothermic peak of combustion moves to the back of combustor as the injection velocity increasing. Too fast injection velocity leads to combustion incompletely. Metal particle diffuses little at radial direction, so chemical reaction near internal face of combustor produces little. And it leads to low temperature that can be used for thermal protection.
出处
《计算机仿真》
CSCD
北大核心
2013年第6期99-102,238,共5页
Computer Simulation
基金
西北工业大学基础研究基金资助项目(JC20110205)
关键词
粉末火箭发动机
颗粒粒径
颗粒喷注速度
数值仿真
：Powdered rocket motor
Particle diameter
Particle injection velocity
Numerical simulation
