The Confirmation of Thermal Boundary Parameters in an Oxygen Kerosene Fuel-Rich Rocket Engine

The thermal environment is an important factor in the design of liquid rockets. In this paper, theoretical analysis, numerical simulation and experimental testing are conducted to study boundary characteristics a GOX/kerosene rocket motor with total flow rate 120 g/s oxygen-fuel ratio 1:1. We measured axial temperature different positions combustor using thermocouples heat flux meter. found that at 182 mm increases by 6.8% when carbon deposit exists. For results, after correcting conductivity volume fraction deposition, (1.11 MW/m2, corrected conductivity) result (0.89 considering injectors) similar value (0.937 MW/m2). This validates accuracy calculation case, provides verification data for future calculation, as well setting gas wall phase.