Due to high efficiency and lack of contaminants resulting from cryogenic engines combustion as well as high energy content of these motors they are increasing used for space shuttle engines. So, this clarifies the necessity of more analysis of these fuels besides improving the efficiency of internal combustion engines. Prediction of transport phenomena in liquid rocket engines because of some complexities was impossible to be done, but today it happens via using the simulation software. The present research is an attempt to examine the results of modeling and simulation of flow field and the temperature inside the combustion chamber with liquid fuel applying the combustion models in combination with the turbulence models. The simulation results and turbulence model predicted well the temperature inside the combustion chamber. Also, with regard to the simulation results of the combustion chamber, the effects of change of geometric parameters of the cooling ducts on transfer of the engine thrust chamber with liquid fuel. These geometrical parameters include number and frequency of the cooling channels height, fins thickness and the inner wall of the drift chamber. The results indicate that with decrease of flowing cross section of refrigerants from the channel and reduction of the thickness of the inner wall chamber, the wall temperature will also reduce. As the maximum wall temperature occurs in the throat area, increasing the number of cooling channels has a direct impact on the reduction of the maximum wall temperature, but with increase of the height, the maximum wall temperature will increase.