Numerical Simulation of Liquid Film in a Liquid Oxygen/Rocket Propellant 1 Liquid Rocket

The numerical simulation of the liquid film in a liquid oxygen/rocket propellant 1 (LO x /RP ― 1) liquid rocket was conducted using time-averaged Navier-Stokes equations and the standard k-e model for compressible steady three-dimensional flow. The RP-1 combustion kinetics mechanism of 10 components and 17 step reactions was used in the eddy-dissipation-concept model. The results show that the film-cooling effectiveness is higher with the greater mass flow rate of the RP-1 film and that adding the radial angle of the film hole is helpful for enhancing the film-cooling effectiveness at the beginning of the combustor chamber. To achieve lower carbon deposition at the throat of the nozzle and higher cooling effectiveness, RP-1 film mixed with 5―10% H 2 or H 2 O is proposed as a new type of cooling film in this paper. After 10% H 2 or 10% H 2 O is added to the RP-1 film, the film-cooling effectiveness is improved by 20.3% or 11.8%, respectively. Moreover, the liquid film decreases the nozzle-specific impulse by no more than 2.33%.