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为了计算固液混合式火箭冲压发动机补燃室内的三维反应流场 ,用块隐式法求解气相Navier Stokes方程组 ,用连续介质模型和k ε Ap 模型计算颗粒相的湍流流动与蒸发过程 ,用修正的k ε g模型描述燃料的燃烧。为了分析发动机设计参数对反应流场的影响 ,用不同的条件进行计算 ,并由此分析了补燃室几何结构和液体燃料初始颗粒直径对燃烧效率的影响。算例表明 ,计算方法有效可行 ,数值结果能够反映流场结构、液体燃料的蒸发和两种燃料的燃烧过程。
In order to calculate the three-dimensional reaction flow field in the afterburner of solid-liquid hybrid rocket ramjet engine, the Navier-Stokes equations were solved by implicit block method and the turbulent flow and evaporation process of particle phase were calculated by continuous medium model and k ε Ap model. The modified k ε g model describes the combustion of the fuel. In order to analyze the influence of engine design parameters on the flow field of the reaction, different conditions were used to calculate the influence of combustion chamber geometry and the initial particle diameter of liquid fuel on the combustion efficiency. The example shows that the calculation method is effective and feasible. The numerical results can reflect the structure of the flow field, the evaporation of the liquid fuel and the combustion process of the two fuels.