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

作　　者：万律强 李双菲 陈彦君 WAN Lüqiang;LI Shuangfei;CHEN Yanjun(School of Mechanical Engineering,Guangxi University,Nanning 530004,China;Shanghai Aerospace System Research Institute,Shanghai 201109,China)

机构地区：[1]广西大学机械工程学院,南宁530004 [2]上海宇航系统工程研究所,上海201109

出　　处：《航天器环境工程》2025年第2期144-151,共8页Spacecraft Environment Engineering

基　　金：上海市“科技创新行动计划”启明星项目(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)。

摘　　要：可重复使用火箭发射至回收期间,其尾焰中的富燃燃气会与空气中的氧气发生二次燃烧。为快速分析二次燃烧对火箭箭体热环境的影响,建立了一个适用于描述液氧/甲烷火箭尾焰二次燃烧的化学动力学机理模型。利用DRGPFA方法剔除Gri-Mech 3.0机理模型的冗余组分及反应,根据文献实验值对计算结果进行验证,并分析了环境参数(压力和温度)对燃烧过程的影响;继而通过温度敏感性分析得到简化的10组分14步及9组分7步反应机理模型。结果表明,环境参数对燃烧过程有显著影响,且各简化模型计算值在不同反应器模型中的变化趋势一致性良好。所建立的简化机理模型能够有效预测二次燃烧区域的温度场、自由基分布和热释放特性,可为可重复使用火箭热防护设计提供理论依据和计算工具。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-Mech 3.0机理模型 敏感性分析 简化机理 

分 类 号：TK16[动力工程及工程热物理—热能工程] V434.13[航空宇航科学与技术—航空宇航推进理论与工程]