Abstract
This study is on combustion modelling of gaseous hydrogen and cryogenic liquid oxygen at subcritical condition for well-known Mascotte laboratory combustor. The proposed strategy relies on hybrid Eulerian-Lagrangian framework in which the continuous phase is evaluated by Reynolds Average Navier-Stokes (RANS) equations and quick discretization method. The dispersed phase of combustion field is evaluated by Discrete Phase Method (DPM). The Eddy Dissipation Concept (EDC) has been performed for combustion-turbulence interaction modelling. Effects of turbulence model, chemical kinetic mechanism, equation of state, and inlet momentum jet flux are investigated in terms of combustion field characteristics. The accuracy of predictions is identified through a detailed comparison with the experimental databases gathered on the ONERA Mascotte test bench. Results show that predictions using the turbulence model family, consists of Standard and RNG models, are closer to the measurements. In order to investigate effect ...
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