摘要
本文采用CSP方法得到的7组分/4反应简化机理对二维超声速气流中氢气自点火过程进行了数值模拟,计算得到的壁面压力数据与实验结果具有一定的可比性。针对计算结果进行了动力学分析,得到着火过程的反应路径和重要自由基变化,与总包机理相比获得了更加详细和准确的着火及燃烧过程信息,再现了详细动力学模型,而与直接采用详细机理计算相比大幅提高了计算效率,从而证实了CSP简化机理应用于超声速燃烧的可靠性和优越性。
Obtained with computational singular perturbation （CSP） method, a reduced mechanism including 7 species and 4 reactions was implemented into the simulation of auto-ignition and combustion of hydrogen in the supersonic flow. The computational results of pressure distribution along the wall were comparable with experimental results. According to the calculation results, analysis of reaction kinetics was made in the process of ignition and combustion, including reaction paths and important radical changes. Compared with 1-step mechanism, reduced mechanism won more detailed and accurate information in the process of reaction, and in comparison with detailed mechanism, calculation efficiency was sharply increased with reduced mechanism, therefore reliability and superiority of CSP reducing method used in supersonic combustion were confirmed.
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
2013年第2期380-383,共4页
Journal of Engineering Thermophysics
关键词
CSP
超声速燃烧
氢气
反应动力学
CSP
supersonic combustion
hydrogen
reaction kinetics
