Fuel Regression Modelling for Hybrid Rocket CFD Simulations
Résumé
A new Gas-Surface Interaction (GSI) model, based on the mass/energy balance at the fuel surface, is implemented in the ONERA Computational Fluid Dynamics (CFD) software CEDRE. The modelling aims at improving, by means of numerical simulations, the knowledge about aero-thermochemical phenomena in hybrid rocket engines. The two-equation turbulence model k-! Shear Stress Transport (SST) is used with wall blowing correction to represent properly the turbulent boundary layer structure which rules the convective transfer and depends on the fuel mass injection. The objective of the study is to validate spatially and temporally the GSI model for H2O2/HDPE HYCAT hybrid rocket engine using a catalytic injector. The validation process is based on the fuel regression rate comparison between numerical CFD results and experimental data from a reference case chosen in the testing campaign of the HYCAT hybrid rocket engine. Particularly, the temporal validation method considers the instantaneous fuel regression rate obtained by a ballistic reconstruction technique from measured instantaneous chamber pressure and oxidizer mass flow rate during the firing test.
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