An example airfoil assembly (20) includes an airfoil body (22) extending between a leading edge, a trailing edge, a suction side, and a pressure side. The assembly further includes a first protective sheath (34), an indicator sheath (72), and a second protective sheath (60). The first protective sheath (34) has an outer side (36) and an inner side (38) that forms a cavity for receiving at least a portion of the airfoil body (22). The inner side being bonded to the leading edge of the airfoil body. A portion of the indicator sheath (72) is positioned forward the first sheath (34) relative to the leading edge of the airfoil. A portion of the second protective sheath (60) is positioned forward the indicator sheath (72) relative to the leading edge of the airfoil.


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    Titel :

    Airfoil assembly and airfoil assembly wear indicating method


    Weitere Titelangaben:

    Verschleissanzeige einer Flugzeugkomponente
    Indicateur d'usure de composant de surface portante


    Beteiligte:
    SMITH BLAIR A (Autor:in) / CARVALHO PAUL A (Autor:in) / HUTH BRIAN P (Autor:in)

    Erscheinungsdatum :

    2020-07-29


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS



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