摘要
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。通过数值模拟得到两种内流场模型各个时刻的压强空间分布信息以及燃烧室前、中、后3个监测点的压强-时间曲线,对比两种模型的计算结果,着重对侵蚀比模型的内流场和药柱内外压强差进行分析,并与试验结果进行对比。结果表明:两种模型最大压强差不超过3%,在平衡压强段后基本一致;侵蚀比模型在发动机工作过程中药柱没有出现明显的侵蚀燃烧喇叭型,前级高压区药柱内外压差最大不超过3.9%,在后级低压区药柱内外压差最大不超过8%;3个监测点的压强-时间曲线与试验数据吻合度较好;研究结果可为类似结构的固体火箭发动机数值模拟提供参考。
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.
作者
周柏航
陶如意
王浩
阮文俊
ZHOU Baihang;TAO Ruyi;WANG Hao;RUAN Wenjun(School of Energy and Power Engineering, Nanjing University of Science and Technology, Nanjing 210094, Jiangsu, China)
出处
《兵工学报》
EI
CAS
CSCD
北大核心
2021年第8期1604-1612,共9页
Acta Armamentarii
基金
军队科研项目(2017年)。
关键词
固体火箭发动机
阶梯多根装药
侵蚀燃烧
三维内流场
solid rocket motor
ladder-shaped multiple charge
erosive burning
3-D inner flow field
