论文部分内容阅读
对颗粒相采用颗粒轨道模型,气相求解可压缩N-S方程组,计算方法采用显式Runge-Kutta时间推进法与有总变差衰减(TVD)性质的高精度MUSCL-Roe格式;自主开发了曲线坐标系下二维轴对称可压缩N-S方程组的解算器Solve2D,研究了固体火箭发动机喷管中颗粒相对流场的影响以及不同尺寸颗粒运动规律.结果表明:颗粒相对流场的影响主要表现在喷管喉部以及扩张段,和单相流场相比,沿轴线马赫数减小,且颗粒尺寸越小减少得越多;沿轴线气相温度升高,且颗粒尺寸越小温度升高越多;颗粒尺寸越小,无粒子区越小;颗粒越大与收缩段壁面碰撞越剧烈,无粒子区越大.
Using the particle orbit model for the particle phase, the NS equations can be solved in the gas phase using the explicit Runge-Kutta time-propulsion method and the high-precision MUSCL-Roe scheme with the properties of total variation attenuation (TVD). The curve coordinates Solve2D, a solver for the two-dimensional axially symmetric and compressible Navier-Stokes equations, was used to study the effect of particles on the relative flow field and the movement of particles with different sizes in the solid rocket motor nozzle. The results show that the relative flow field is mainly affected by Nozzle throat and the expansion of the section, compared with the single-phase flow field along the axis Mach number decreases, and the smaller the particle size decreases more; along the axis gas phase temperature increases, and the smaller the particle size the greater the temperature rise ; The smaller the particle size, the smaller the particle-free area; the bigger the particle collides with the wall of the shrinkage section, the larger the non-particle area is.