Simulation of Stationary Combustion of Cryogenic Propellants in Rocket Combustion Chamber with Porous Injector Head

Kurzfassung

The stationary combustion of cryogenic propellants (H2 and LOx) is simulated in a rocket combustion chamber with a porous injector head. Turbulent combustion is modelled with the use of the eddy dissipation model and of the extended coherent flame model. Both models are extended in order to capture the features of the flame of cryogenic hydrogen and oxygen at high pressure. The numerical simulations have a good agreement with experimental results. At the current stage the eddy dissipation model shows the better results at the condition of the current work as the more sophisticated extended coherent flame model.