Parameters such as fuel injector orientation, fuel flow rate, and stagnation temperature affect scramjet engine operation. In this work, three fuel injection methods were used to supply the combustor of a generic cavity-based scramjet flowpath with gaseous ethylene: upstream normal (up1), upstream angled (up2), and downstream normal (down1). Various combinations of fuel flow rates and fuel injection methods were explored using two stagnation temperatures ( T 0   =   475    K and T 0   =   700    K ) and one stagnation pressure ( P 0   =   345   kPa ) for a Mach-1.8 facility nozzle. The pre-ignition local equivalence ratio ( Φ ) in the cavity was leaner and less sensitive to global Φ with up1 fueling than up2 fueling. For reacting conditions, up1 fueling required a higher global Φ than up2 fueling to obtain the same specific stream thrust metric, calculated from pressure measurements along the flowpath. Redistributing fuel from up2 to down1 resulted in a lower specific stream thrust metric, but redistribution from up1 to down1 produced a higher specific stream thrust metric. The range of attainable global Φ s shifted to richer values with a step increase in stagnation temperature due to the reduced ratio of heat release from a given quantity of fuel relative to the total flow enthalpy.


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    Titel :

    Effect of Fuel Injection Strategy on Generic Scramjet Combustor Operation


    Beteiligte:

    Erschienen in:

    Erscheinungsdatum :

    01.03.2025




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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