摘要
本文对变推力液体火箭发动机喷注器通道内介质流动进行求解。简化解析解直观反映了喷注器几何参数、工作参数以及介质物性参数如何影响推进剂流量、流量系数和最大出口速度等量。采用SIMPLE算法的数值解,模拟了通道内的层流与湍流流动。将数值解与实验结果比较表明,根据流态合适地选用数值模型可以较好地模拟喷注器通道内的流动过程。
Flow in injector passages of a variable thrust liquid propellant rocket engine was studied. The results of a simplified analytical solution show the influence of geometric parameters, operational parameters and the physical property parameters of the medium on propellant flow rate, flowrate coefficient, the maximum exit velocity. The laminar and turbulent flows in the passages have been simulated numerically by SIMPLE method. By comparing the numerical results with experimental ones, it has been shown that the numerical model, which is properly selected according to flow state, can simulate well the flow process in the passages of the injector.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
1990年第2期97-102,共6页
Journal of Astronautics
关键词
喷注器
液体火箭
发动机
数值计算
Liquid propellant rocket engine, Injector, Numerical calculation,
