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为了预估超燃冲压发动机燃烧室内的释热分布,针对带凹腔稳焰器的燃烧室,总结了射流混合情况、来流温度和当量比对释热分布影响的实验规律,提出了主燃烧区的概念和分段线性拟合的建模思路。模型被分为隔离段、横向射流、燃烧室释热分布、主燃烧区反压四个部分。通过压力前推,进行代数的迭代计算,能够快速得到燃烧室释热分布的一维模型。利用实验图像和仿真计算数据,对模型得到的释热分布与燃烧效率进行了验证,模型可适用于隔离段来流2.1马赫以上的工况,且模型结果与仿真结果相关系数达到了0.9以上。
In order to predict the distribution of heat release in the combustion chamber of a scramjet, the experimental laws of jet mixing and the effect of flow temperature and equivalence ratio on the distribution of heat release were summarized. The main combustion The concept of region and the modeling idea of piecewise linear fitting. The model is divided into four sections: isolation section, transverse jet, distribution of heat release in combustion chamber and back pressure in the main combustion zone. Through the pressure forward, iterative calculation of algebra, can quickly get the combustion chamber heat distribution of one-dimensional model. The experimental data and simulation data are used to verify the distribution of heat release and combustion efficiency of the model. The model can be applied to the condition of Mach 2.1 and above, and the correlation coefficient between model and simulation results reaches 0.9.