The invention relates to a propelling nozzle for a turbofan engine on a supersonic aircraft, the propelling nozzle comprising: a propelling nozzle wall (20), a duct (15), which is radially outwardly bounded by the propelling nozzle wall (20), and a central body (5) arranged in the duct (15). According to the invention, the central body (5) is connected to the propelling nozzle wall (20) via at least one brace (31, 32).


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    Titel :

    PROPELLING NOZZLE FOR A TURBOFAN ENGINE ON A SUPERSONIC AIRCRAFT


    Beteiligte:

    Erscheinungsdatum :

    18.03.2021


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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