Abstract: 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.