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首页> 外文期刊>International journal of hypersonics >Effect of Injection Angle in Mixing and Combustion Characteristics of Scramjet Combustor
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Effect of Injection Angle in Mixing and Combustion Characteristics of Scramjet Combustor

机译：喷射角度对超燃喷射燃烧室混合燃烧特性的影响

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Effect of injection angle in mixing and combustion in a scramjet combustor is numerically simulated. Three dimensional Navier Stokes equations alongwith k-e turbulence model are solved using commercial CFD software. Both infinitely fast rate kinetics and single step finite rate kinetics are used to model chemical kinetics. Turbulence chemistry interaction is modeled by Eddy Dissipation Concept (EDC). Good agreement between the computed and experimental results for angular injection (30°) and perpendicular injection forms the basis of further analysis. More flow blockage has caused significant upstream interaction for perpendicular injection and terminal shock is seen to anchor upstream of combustor step; while for angular injection, the flow field is predominantly supersonic. Single step finite rate chemistry show comparatively low pressure and lesser upstream interaction because of the presence of backward reaction. Thermochemical variables are analysed to study the effect of angle of injection on nature of combustion (whether premixed or diffusive), heat release pattern, combustion efficiency etc.
机译：数值模拟了喷射角对超燃燃烧室混合和燃烧的影响。使用商用CFD软件求解三维Navier Stokes方程以及k-e湍流模型。无限快速率动力学和单步有限速率动力学都用于模拟化学动力学。湍流化学相互作用由涡流消散概念（EDC）建模。角注入（30°）和垂直注入的计算结果与实验结果之间的良好一致性构成了进一步分析的基础。更大的流量阻塞导致垂直喷射产生明显的上游相互作用，并且可以看到末端冲击会固定在燃烧室台阶的上游。对于角射流，流场主要为超音速。由于存在反向反应，单步有限速率化学反应显示出较低的压力和较小的上游相互作用。分析热化学变量以研究喷射角度对燃烧性质（无论是预混合还是扩散），放热模式，燃烧效率等的影响。

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