固液火箭冲压发动机内两相反应流场数值计算(英文)

Computation of two-phase reacting flows in solid-liquid rocket ramjets

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 compute three-dimensional reacting flow fields established in the chambers of solid-liquid rocket ramjets, the block implicit algorithm was used to solve the Navier-Stokes equations about gas, the Continuum Formulation Model and k-Ε-Ap model were used to characterize the turbulent flow and vaporization of droplets. The modified k-Ε-g model was adopted to represent the combustion of the fuels. Calculations were carried out under different chamber configurations and initial droplet diameters, from which the effects of these conditions on the combustion efficiency were analyzed. The numerical results reveal the processes of droplet vaporization and combustion.