Numerical simulation has been done for liquid film cooling in liquid rocket combustor.Multiple species of axial Navier-Stokes equations have been solved for liquid-film/hot-gas flow field

and k-ε equations have been used for compressible turbulent flow.The results of the model agree well with the results of software FLUENT.The results show that:(1) Liquid film can decrease the wall heat flux and temperature effectively

and the cold border area formed by the film covers the whole combustor and nozzle wall.(2) The turbulent viscosity is higher than the physical viscosity

and its biggest value is in the border area of the convergent area in nozzle.The effect of turbulent flow on the whole simulation field can not be ignored.(3) The mass fraction of kerosene at the film inlet is 1

but it decreases along the nozzle wall and achieves its lowest value at the outlet.However

the mass fraction of kerosene near the wall is the biggest at any axial location.