Consistent flamelet-based turbulent combustion modeling for liquid rocket engines

In this work we present a consistent flamelet-based framework for turbulent combustion modeling in liquid rocket engines. This approach is based on the low- Mach number approximation of the governing equations and on the tabulation of all the thermochemical properties by means of steady laminar flamelets. The proposed framework features the possibility to accommodate, in a computationally efficient manner, real gas thermodynamics and to account for non-adiabatic combustion in the presence of wall heat transfer. Such capabilities are tested separately on two well-established experimental configurations consisting in methane-oxygen flames at elevated pressures, by means of unsteady Reynolds averaged Navier Stokes simulations.