Abstract:

For rapid cooling the rocket exhaust gas with water injection, the mooring ignition and the cooling effect with water injection are tested for a sub-scale rocket engine. The distribution of the impinging jet and the two-phase flow with water injection are studied, and the cooling effect is also compared by collecting the temperature data of the two flow states. By studying the heat and mass transfer mechanism of the gas-liquid two-phase flow theory under the high temperature and high speed convection impact conditions, a program to solve the mass and energy transfer based on the mixture multiphase model is added into the unsteady gas-liquid two-phase flow field model. Verified by the experiment, the results show that the numerical model has higher calculation accuracy and reliability, and the physical phenomenon of water injection into the jet flow can be reflected accurately. Through the numerical simulation, the three main components including the rocket exhaust gas, the liquid water and the water vapor are analyzed, and the envelope size such as length and width of the jet flow and the temperature data are analyzed by comparing with the free jet flow field. The cooling effect is conspicuous with water injection.

Key words: Jet flow, Water injection, Vaporization effect, Two-phase flow, Subscale test