Reduced-order modeling of the thermodynamic cycle within a rotating detonation engine system is presented with an emphasis on the identification of the parameters that drive performance and the validation of the model with computational and experimental test results. Treatment of propellant injection and the balancing of pressure and mass flow through the engine are presented. A focus is placed on the identification of the parameters that drive performance in a rotating detonation device, such as deflagration of reactants, while noting those that have little impact, which include reduced detonation velocity due to lateral area relief. A thermodynamic description of the rotating detonation engine is proposed, using traditional cycle analysis methods in an effort to develop an initial design and performance tool for such pressure gain combustion devices.


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    Titel :

    Thermodynamic Modeling of a Rotating Detonation Engine Through a Reduced-Order Approach



    Erschienen in:

    Erscheinungsdatum :

    2017




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch



    Klassifikation :

    BKL:    55.50 Luftfahrzeugtechnik / 55.50
    Lokalklassifikation TIB:    770/7040



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