喷注器通道流动解析解和数值解

ANALYTICAL AND NUMERICAL SOLUTIONS OF FLOW IN INJECTOR PASSAGES

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.