Numerical simulation of liquid film and regenerative cooling in a rocket combustor

Numerical calculation was made for liquid film and regenerative cooling in a liquid rocket combustor. Multiple species axial Navier-Stocks(N-S) equations were solved for liquid-film/hot-gas flow field, single specie axial N-S equations were solved for regenerative flow field and k-Ε equations for turbulent flow. A kerosene/LOx rocket combustor was simulated, and the results of the model agreed well with the results in reference. The results show that: (1) Liquid film and regenerative cooling decrease the wall flux and wall temperature effectively, and the cold area covers the whole combustor and nozzle wall. (2) The cooling effect becomes better with the increase of the regenerative coolant. (3) The temperature rise of the regenerative coolant is between 450~600 K, and becomes smaller when the mass flow rate of the regenerative coolant is larger. (4) The mass fraction of kerosene on the inner wall decreases along the axis and reaches the lowest value at the outlet, but the area containing kerosene becomes larger.