Two-phase turbulent reacting flow model of the internal operating processes in Liquid Rocket Engine (LRE) is set up in non-orthogonal curvilinear coordinates.By means of this model

numerical simulation of the combustion flow process in LO x/GH 2 test rocket engine has been accomplished.From the simulation

velocity patterns

contour maps of gas species concentration

temperature

pressure

Mach number

combustion efficiency

and plots of wall temperature and average radiateion temperature

and plot of spray vaporization are obtained.