Abstract
Combustion in liquid rocket engines happens under severe thermodynamical conditions: pressure exceeds the critical pressure of injected propellants and temperature is cryogenic. Such a situation requires an important effort of modeling: real gas effects are incorporated through cubic equations of state along with pressure-correction terms, and transport properties follow specific rules. Modeling for turbulent combustion is also an issue. A way to introduce finite rate chemistry and real gas effects into LES is the use of tabulated thermochemistry because the number of transported variables is then reduced compared to a multi species formulation. This model is used to perform the large-eddy simulation of a co-axial CH4-LOx injector operating at supercritical pressures. The computed flame length is in the range of the experimental observations and it is observed that chemical equilibrium is reached well before the outlet of the combustion chamber.
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