航天器环境工程2025，Vol.42Issue(2)：144-151,8.DOI:10.12126/see.2024118
液氧/甲烷火箭尾焰二次燃烧反应机理模型简化研究
Investigation of simplified reaction mechanism model for afterburning of liquid oxygen/methane rocket tail flame
摘要
Abstract
During the launch and recovery phase of the reusable rockets,the fuel-rich exhaust gas in their tail flames will undergo afterburning with the oxygen in the air.To rapidly analyze the impact of afterburning on the thermal environment of the rocket body,a chemical kinetic model suitable for describing the afterburning of liquid oxygen(LOX)/methane rocket tail flames was established.The DRGPFA method was used to eliminate redundant components and reactions from the Gri-Mech 3.0 mechanism model,and the calculated results were verified using experimental data from the literature.The effects of environmental parameters(pressure and temperature)on the combustion process were analyzed.Subsequently,temperature sensitivity analysis was carried out to obtain simplified reaction mechanism models with ten components and fourtenn steps,and nine components and seven steps,respectively.The results demonstrate that environmental parameters have a significant influence on the combustion process,and the calculated values from the various simplified models exhibit consistent trends across different reactor configurations.The simplified mechanism model established in this study can effectively predict the temperature field,free radical distribution,and heat release characteristics in the secondary combustion region,providing a theoretical and computational tool for thermal protection design of reusable rockets.关键词
液氧/甲烷火箭/二次燃烧/Gri-Mech3.0机理模型/敏感性分析/简化机理Key words
LOX/methane rocket/afterburning/Gri-Mech 3.0 model/sensitivity analysis/simplified mechanism分类
能源与动力引用本文复制引用
万律强,李双菲,陈彦君..液氧/甲烷火箭尾焰二次燃烧反应机理模型简化研究[J].航天器环境工程,2025,42(2):144-151,8.基金项目
上海市"科技创新行动计划"启明星项目(编号:22YF1448300) （编号:22YF1448300）
上海航天技术研究院青年博士基金项目 （）
广西壮族自治区自然科学基金青年基金项目(编号:2023GXNSFBA026258) （编号:2023GXNSFBA026258）
