The SSTk-ω turbulence model was used to simulate the coupled whole field of the transpiration cooling of a Laval-nozzle of a liquid O2/H2 propellant rocket engine.The influences of porosity

variation property

compressibility

the thermal disperse effect of porous media

micro-scale flow and mass transfer were considered in the model.The influences of porosity on local blowing ratio

the wall temperature and the boundary layer thickness were analyzed and compared with the regenerative cooling.The results showed that the increase of average blowing ratio can decrease the average wall temperature with a larger proportion and for the transpiration cooling nozzle the throat is no longer the highest temperature point.The simulation results were compared with both the experimental results and the one dimension aerodynamics formula and approved to be accurate.