Numerical simulation of variable thrust engine combustion chamber

The combustion and aerodynamic processes of liquid bipropellants in the combustion chamber of a Variable Thrust Engine(VTE), to be used in the Orbital Maneuvering Vehicle(OMV), have been predicted at the choking condition of two different power level. The computation is conducted from the injector face down to the nozzle throat. Appropriate physical submodels are adopted to account for the two-phase interaction between bipropellant droplet flows and gas-phase flow. The nozzle throat conditions are determined by the mass con. servation and the thermodynamic relations. The optimal atomization condition is suggested V, considering the high combustion performance and the relatively cool chamber. Therefore, the conventional design concept linked with the corollary “the finer the spray, the better the efficiency” must be reassessed.