In this paper, the effect of flight Mach number on the relative performance of pulse detonation engines and gas turbine engines is investigated. The effect of ram and mechanical compression on combustion inlet temperature and the subsequent sensible heat release is determined. Comparison of specific thrust, fuel consumption and impulse for the two engines show the relative benefits over the Mach number range.


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    Titel :

    Role of Air-Breathing Pulse Detonation Engines in High Speed Propulsion


    Beteiligte:

    Kongress:

    52nd International Astronautical Congress ; 2001 ; Toulouse, France


    Erscheinungsdatum :

    01.09.2001


    Medientyp :

    Preprint


    Format :

    Keine Angabe


    Sprache :

    Englisch