带侵蚀燃烧效应的阶梯多根装药火箭发动机三维内流场特性

为研究阶梯多根装药火箭发动机的内流场特性,采用Fluent计算软件对侵蚀比和平均侵蚀比两种内流场模型分别进行全三维数值模拟.基于自定义函数接口编程进行二次开发,提取侵蚀比模型每个节点的坐标和压强以及平均侵蚀比模型每个燃面的平均压强,导入燃速公式和质量流率公式,来控制边界网格的移动速度和单位面积燃气进口质量流率.通过数值...

3-D Inner Flow Field Characteristics of Ladder-shaped Multiple Charge Rocket Motor with Erosive Burning

In order to study the internal flow field characteristics of ladder-shaped multiple charge rocket motor,the full 3-D internal flow field models for erosion ratio and average erosion ratio were numerically simulated using Fluent software. The secondary development was carried out through User Defined Function(UDF) interface programming. The coordinates and pressure of each node of erosion ratio model and the average pressure of each burning surface of average erosion ratio model are extracted, and the formulas of burning rate and mass flow rate are introduced to control the moving velocity of boundary grid and the mass flow rate of gas inlet per unit area. The spatial distribution information of pressures at each moment in two inner flow field models and the pressure-time curves of three monitoring points in the front, middle and rear of combustion chamber were obtained through numerical simulation. The calculated results of the two models are compared.The inner flow field and the pressure difference between the inside and outside of grain in the erosion ratio model are analyzed. The results show that the maximum pressure difference between the two models is no more than 3%, which is basically the same after the equilibrium pressure section. There is no obvious erosive burning trumpet type in the erosion ratio model during the working process of motor. The maximum pressure difference between the inside and outside of grain in the front high pressure area is not more than 3.9%, and is not more than 8%in the rear low pressure area. The pressure-time curves of the monitoring points is in good agreement with the test data.