The aim of the present work is the investigation of the combustion phenomenon in liquid-propellant rocket engines. The combustion of liquid oxygen and gaseous methane in a shear coaxial injector under supercritical pressure was analyzed. To realize an efficient numerical description of the phenomena, it is important to treat the LOx jet in a manner which takes into account its real behavior. In the present work different kinetics, combustion models and thermodynamics approaches were used in association with the description of the jet as a discrete phase. For all the approaches used, a comparison with experimental data from literature was performed.
- International Gas Turbine Institute
Spray and Combustion Modeling in High Pressure Cryogenic Jet Flames
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De Giorgi, MG, Sciolti, A, & Ficarella, A. "Spray and Combustion Modeling in High Pressure Cryogenic Jet Flames." Proceedings of the ASME Turbo Expo 2012: Turbine Technical Conference and Exposition. Volume 2: Combustion, Fuels and Emissions, Parts A and B. Copenhagen, Denmark. June 11–15, 2012. pp. 1161-1176. ASME. https://doi.org/10.1115/GT2012-69544
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