氢气化学反应机理在超声速燃烧数值仿真中的应用研究  

Application of hydrogen chemical reaction mechanism in numerical simulation of supersonic combustion

作　　者：田亮[1,2] 张世毅 王洪信 朱韶华 Tian Liang;Zhang Shiyi;Wang Hongxin;Zhu Shaohua(School of Energy and Environmental Engineering,Hebei University of Technology,Tianjin 300401,China;Hebei Key Laboratory of Thermal Science and Clean Energy Utilization Technology,Tianjin 300401,China;School of Engineering and Design,Technical University of Munich,Munich 80333,Germany;School of Astronautics,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]河北工业大学能源与环境工程学院,天津300401 [2]河北省热科学与能源清洁利用技术重点实验室,天津300401 [3]慕尼黑工业大学工程与设计学院,慕尼黑80333 [4]西北工业大学航天学院,西安710072

出　　处：《空天技术》2024年第3期11-23,共13页Aerospace Technology

摘　　要：针对一种支板构型超燃燃烧室开展了氢燃烧的化学反应动力学机理在超声速燃烧中的适用性研究,在选取了合适的湍流模型和反应模型后,研究了8种化学动力学机理(5种详细机理和3种简化机理)在相同工况下的超声速燃烧流场。对比了将3种湍流模型和2种反应模型组合后得到的仿真结果与实验数据,发现选用SST k-ω湍流模型和EDC反应模型进行支板型发动机燃烧室流场仿真最合理。通过对比使用5种详细机理模拟得到的燃烧室流场截面上温度、速度、OH浓度和H_(2)O质量分数分布情况,发现结果中OH浓度分布有较大差别,其他参数差别不大;对比分析了使用简化机理得到的模拟结果与详细机理,发现3种简化机理得到的火焰结构、火焰温度和中间产物OH的分布都与详细机理差别很大。The applicability of the chemical reaction kinetics mechanism of hydrogen combustion to supersonic combustion is studied for a supersonic combustion chamber with support plate configuration.After selecting suitable turbulence model and reaction model,the supersonic combustion flow field of 8 chemical dynamics mechanisms(5 detailed mechanisms and 3 simplified mechanisms)under the same working condition is studied.By comparing the simulation results of three turbulence models and two reaction models with the experimental data,it is found that the most reasonable choice of SST k-ωturbulence model and EDC reaction model is to simulate the flow field of the combustion chamber of the supported plate engine.By comparing the distribution of temperature,velocity,OH concentration and H_(2)O mass fraction on the cross section of the combustion chamber flow field simulated by five detailed mechanisms,it is found that the OH concentration distribution in the results is quite different,and other parameters are not very different.The simulation results obtained by the simplified mechanism are compared with those obtained by the detailed mechanism,and it is found that the flame structure,flame temperature and the distribution of intermediate product OH obtained by the three simplified mechanisms are very different from those obtained by the detailed mechanism.

关 键 词：支板型超燃冲压发动机 化学动力学机理 氢气 简化机理 数值模型 

分 类 号：V231.21[航空宇航科学与技术—航空宇航推进理论与工程]