Comparison of LOX/Methane and LOX/Hydrogen cryogenic spray combustion with simultaneous optical diagnostics
Résumé
ONERA and CNES are collaborating to prepare the next engine generation for reusable launchers that
will use liquid oxygen (LOX) and methane (CH4) as propellants. The present experimental study was
carried out on the MASCOTTE test bench located at ONERA, Palaiseau center. The main goal was to
characterize the LOX jet, under reacting conditions, with simultaneous droplet-size measurements and
high-speed chemiluminescence and shadowgraphy visualizations for two propellant couples:
LOX/CH4 and LOX/H2, under similar operating conditions. High-speed visualizations were used to
assign the locations of drop-size measurements obtained in the cryogenic jet flames, to explain the
results and to analyse the peculiarities of combustions with both propellants.
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