A gas turbine engine designed to take-off and land as a conventional turbofan engine at subsonic speeds and accelerate to supersonic speeds during flight by converting into a hybrid turbojet and ramjet engine. This is achieved by introducing an afterburner in the bypass duct of the engine and by retracting the bypass fan backward into a cylinder. This operation is carried out before the aircraft enters the transonic regime, at any stage below Mach 1. At supersonic speed, the shock wave is deflected through a needle cone that is projected out of the nose of the engine in order to prevent the intake air from being choked.


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    Titel :

    A supersonic turbofan engine


    Erscheinungsdatum :

    12.08.2020


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



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