In order to research the gas-liquid two-phase flow problem considering vaporization phenomenon for the rocket engine

the vaporization mechanism of liquid water was studied. The vaporization model for water was established according to the saturation temperature of water at different pressures. A program to solve the vaporization phase change process for liquid water was written on the basis of vaporization model

and the vaporization phase change calculation results were added to the multi-phase flow field equations as vaporization component source term and heat source term

so the three-dimensional multiphase flow field numerical solution considering the liquid water vaporization phase change was realized. Combining with the classical example

the errors of the temperature calculating values and experimental values of the two-phase flow field for the feature points were controlled within 8.5%

verifying the reliability of the three-dimensional calculation of the program. The mass conversion rate curves of two-phase from the different distance of the rocket nozzle showed that the mass conversion rate of two-phase rose from the lowest value to the highest value and then decreased to the lowest value

the transformation mechanism of the liquid and gas phases was revealed. The method can provide direct reference for the vaporization and cooling of the water chamber in the launching stage of launch platform for launch vehicle.