固体火箭发动机燃烧室冷态突扩气固多相流动的数值模拟
Numerical simulation of sudden expansion gas-solid flows in cooling combustor of rocket engine
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摘要: 基于欧拉-欧拉双流体方法，建立固体火箭发动机燃烧室轴对称突扩气固多相流动的统一二阶矩两相湍流模型，采用k-ε双方程模拟气相湍流流动和颗粒相湍流雷诺应力kpg方程描述大尺度颗粒湍流运动、小尺度颗粒各向异性弥散特性以及气固相间作用。数值模拟了突扩流动中的颗粒轴向、径向平均速度和脉动速度以及颗粒-气相脉动速度关联轴向分量的分布特性，计算结果与试验吻合较好。研究结果表明：颗粒轴向速度脉动大于径向速度脉动，轴向平均速度梯度影响脉动速度峰值的发生位置和大小；两相脉动速度关联轴向分量大约是径向分量的2倍。Abstract: A unified second-order-moment two-phase turbulence model (USM) is established for simulation of sudden expansion gas-solid flows in cooling combustor of rocket engine, based on Euler-Euler two phase flow method. In the model, k-εtwo equations are applied for modeling gas turbulence, Reynolds stress kpg equation is used for describing large-scale turbulent movement and small scale anisotropic characters of particles and interactions between gas and particles phase. The distribution behavior of the axial and radial mean velocities, fluctuation velocities and two-phase fluctuation axial velocity correlations of particles are simulated numerically and the results are found to agree with experiments well. It is shown that the axial fluctuation velocity of particles is larger than radial one, the gradient of the axial mean velocity affects the occurring position and the peak value of the fluctuation velocity. The axial component of the two-phase fluctuation velocity correlation is twice as the radial one.
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Keywords:
- combustor
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