| 摘要: |
| 用流动项与化学反应生成源项解耦处理的化学非平衡流动计算方法,从薄层近似三维N S方程出发,采用ENO差分格式数值模拟了超声速冲压加速器简化模型中,高速甲烷气流从后体多个喷口射入高超声速空气流形成流场,研究了高温异质气体效应和19组分65反应模型的非平衡效应对冲压加速器表面压力分布的影响。计算表明新型解耦方法适合反应机理复杂的碳氢燃料超燃冲压发动机内部流动模拟,为开发应用软件系统打下基础。 |
| 关键词: 冲压喷气发动机 非平衡流 反应动力学 烃类燃料 超音速燃烧 计算流体动力学 |
| DOI： |
| 分类号:V235 |
| 基金项目: |
|
| Numerical study for CH4/air supersonic combustion |
|
LIU Jun
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Inst. of Aerospace and Material Engineering, National Univ. of Defence Technology, Changsha 410073, China
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| Abstract: |
| The flow induced by CH4 jets for simplified scramjet model was simulated numerically, based on the 3-D thin-layer approximation N-S equations and ENO scheme. The pressure distribution of scramjet was compared with cases without CH4 jets and chemical reaction. There were 19 species and 65 reactions chemical mechanism in computation. The method was convenient to modify chemical mechanism without changing fluid dynamic codes and was validated to fit for the flow simulation of carbon/hydrogen fuel combustion in scramjet. |
| Key words: Ramjet engine Nonequilibrium flow Reaction kinetics Hydrocarbon fuel Supersonic combustion Computational fluid dynamics |
