The present invention relates to a gas turbine engine fan blade containment system including a shield (318) to be coupled to an aircraft structure (302) and to at least partially surround a circumference of an aircraft engine (100). The shield (318) is to be spaced from an outer surface (102) of the aircraft engine (100) when coupled to the aircraft structure (302). The shield (318) forms a laminated clevis (606) at an end (326) of the shield (318). A retention rod (608) is positioned in the laminated clevis (606) of the shield (318). The retention rod (608) is to engage a lug hook (602) of the aircraft structure (302) to anchor the shield (318) to the aircraft structure (302). The present containment system may be integrated with the airframe completely external to the engine, enabling aircraft manufacturers to select optimal engines independently of the presence of internal fan blade containment.


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    Titel :

    GAS TURBINE ENGINE FAN BLADE CONTAINMENT SYSTEMS


    Weitere Titelangaben:

    EINDÄMMUNGSSYSTEME FÜR GASTURBINENGEBLÄSESCHAUFELN
    SYSTÈMES DE CONFINEMENT D'AUBE DE SOUFFLANTE DE TURBINE À GAZ


    Beteiligte:

    Erscheinungsdatum :

    2020-09-16


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS



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