固体火箭发动机喷管材料烧蚀仿真及分析  

Simulation and Analysis of Nozzle Material Erosion in Solid Rocket Motor

作　　者：康昊 罗忠[1,2] 武生茂 张维维 KANG Hao;LUO Zhong;WU Sheng-mao;ZHANG Wei-wei(School of Mechanical Engineering&Automation,Northeastern University,Liaoning Shenyang 110819,China;Key Laboratory of Vibration and Control of Aero-Propulsion System Ministry of Education,Northeastern University,Liaoning Shenyang 110819,China;Dynamic Machinery Institute of Inner Mongolia,Inner Mongolia Hohhot 010010,China)

机构地区：[1]东北大学机械工程与自动化学院,辽宁沈阳110819 [2]东北大学航空动力装备振动及控制教育部重点实验室,辽宁沈阳110819 [3]内蒙动力机械研究所,内蒙古呼和浩特010010

出　　处：《机械设计与制造》2023年第8期113-116,共4页Machinery Design & Manufacture

基　　金：装备预先研究基金项目(61407200107):基于数值模拟的固体发动机优化设计方法及应用。

摘　　要：针对固体火箭发动机喷管材料烧蚀问题,分析并比较了碳基材料喷管和钨材料喷管的烧蚀率。通过计算两种喷管材料的热化学反应速率,得到了对应的烧蚀率和热流密度分布特性,并分析了燃烧室压强和温度对喷管烧蚀的影响。结果表明:碳基材料喷管与钨材料喷管的烧蚀分布规律相同,但钨材料喷管的整体烧蚀率更小;燃烧室压强和温度均会提高喷管的烧蚀率。综合考虑材料成本和固体火箭发动机整机重量因素,选用钨材料喉衬可以明显减小喷管关键位置的烧蚀量。Aiming at the problem of erosion of solid rocket motor nozzles,the erosion rates of carbon-based nozles and tungsten nozzles are analyzed and compared.By calculating the thermochemical reaction rates of the nozzles,the corresponding erosion rates and heat flux distribution characteristics were obtained,and the influence of combustion chamber pressure and temperature on nozzle erosion was analyzed.The results indicate that the erosion rates distribution of carbon-based nozzle and tungsten nozzle are the same,but the overall erosion rate of tungsten nozzle is smaller.Both combustion chamber pressure and temperature will increase the erosion rate of the nozzle.Considering the material cost and the weight of solid rocket motor,the tungsten throat liner can obviously reduce the erosion at the critical position of the nozzle.

关 键 词：固体火箭发动机 喷管 烧蚀 热化学反应 数值仿真 

分 类 号：TH16[机械工程—机械制造及自动化] V435.14[航空宇航科学与技术—航空宇航推进理论与工程]