An airbreathing pulse detonation engine-crossover system is developed to characterize the feasibility of shock-initiated combustion within an airbreathing pulse detonation engine. A shock wave is transferred through a crossover tube that connects a spark-ignited driver pulse detonation engine to the airbreathing, driven pulse detonation engine. Detonations in the driven pulse detonation engine develop from shock-initiated combustion caused by shock wave reflection. The pulse detonation engine-crossover system increases system efficiency through decreased deflagration-to-detonation transition distance while employing a single spark source to initiate a system consisting of multiple detonation tubes. The initiation effectiveness of shock-initiated combustion is compared to spark discharge initiation and detonation injection through a predetonator. Increasing the Reynolds number enhances combustion wave acceleration. However, for all initiation methods, the system requires a device to transition the combustion wave to a detonation. Shock-initiated combustion and predetonator initiation produce comparable detonation transition runup lengths. With an incident shock wave Mach number of MS=2.36, the runup length is decreased by up to 61% compared to the spark discharge method. Similar combustion evolution is observed for an incident shock wave of strength MS=1.87.


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    Titel :

    Shock-Initiated Combustion in an Airbreathing, Pulse Detonation Engine-Crossover System



    Erschienen in:

    AIAA journal ; 54 , 3 ; 936-949


    Erscheinungsdatum :

    2016




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :

    Klassifikation :

    BKL:    50.93 / 55.50 Luftfahrzeugtechnik / 50.93 Weltraumforschung / 55.60 Raumfahrttechnik / 55.50 / 55.60
    Lokalklassifikation TIB:    770/7040



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