Numerical simulation of the temperature distribution in the turbo-pump system of a rocket engine during gliding

A model based on lumped parameter method was developed for numerical simulation of the temperature distribution in the turbo-pump system. A method for resolving the discharging process of remainder oxidant in pump room was also presented. An example simulation was implemented for parts of the turbo-pump system of a liquid rocket engine during gliding before the second start-up of the engine. The simulation results agree well with the experimental data. It is showed that during gliding, the temperature of turbo decreases, while the temperature of pump and inlet tube increases. The remainder oxidant in pump room exhausts discontinuously. It can be seen that temperature for the turbo, pump and inlet tube is higher than 100°C and the quality in pump room is 1 at the end of gliding, obviously, which can not meet conditions of the second start-up.