Active Control Simulation of Rocket Combustion Instability

Abstract

[Abstract] The active control technology for preventing the combustion instability in a liquid rocket engine has been developed. Aiming at the liquid rocket engine combustion process, the integrated physical model and calculation model was presented. Then the numerical simulation of the combustion instability in the tripropellant liquid rocket engine has been conducted by studying the control equation and physical model of turbulent twophase chemical reaction flow for the combustion process. The results show that combustion instability may be restrained when the proportion of hydrogen is increased, however, it is introduced more easily for smaller average diameter of droplet and too high or too low eject velocity. Finally, According to real time adjusting of propellant flow based on the variety of combustor pressure, combustion instability is controlled actively. The simulation results show that it is feasible that combustion instability of liquid rocket engine can be controlled actively by adjusting propellant flow flux. Nomenclature U = axial velocity respectively V = radial velocity respectively ρ = density T = temperature Sϕ = source terms due to coordinator transform Sd,ϕ = source terms due to two phase flow SC,ϕ = source terms due to chemical reaction P