Shock tunnel experiments are presented that examine combustion modes of ethylene and a 64/36% ethylene/methane mixture under Mach 8 flight-representative conditions within an axisymmetric scramjet cavity combustor. Combustion modes (scram-mode and dual-mode) are presented via streamwise pressure measurements and visualized via planar laser-induced fluorescence (PLIF) of the hydroxyl (OH) combustion radical in the combustor exhaust plume. Ethylene-fuelled experiments developed scram-mode combustion under lean fuelling, whereas increased fuelling anchored combustion to the fuel injector wake. Further fuelling increases to stoichiometric levels developed dual-mode combustion. Exhaust OH PLIF indicated ethylene scram-mode combustion developed combustion products primarily in the wall-adjacent regions, whereas asymmetric flowfields were noted for the dual-mode. The addition of methane inhibited reactions, with no scram-mode combustion observed at even fuel-rich conditions. Higher fuelling rates developed dual-mode combustion with comparable pressure rises to the ethylene-fuelled dual-mode cases. OH PLIF indicated reduced concentration of OH for the ethylene/methane mixture. This work confirms the retarding influence of methane upon the reaction pathways of ethylene and reaffirms that fuels do not react independently in gaseous mixtures.


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    Titel :

    Experimental Scramjet Combustion Modes of Hydrocarbon Mixtures at Mach 8 Flight Conditions



    Erschienen in:

    AIAA Journal ; 58 , 12 ; 5117-5122


    Erscheinungsdatum :

    2020-10-15


    Format / Umfang :

    6 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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