A nacelle inlet structure (30) for an aircraft propulsion system (20). This nacelle inlet structure (30) includes an inlet lip (52), a bulkhead (56) and a reinforcement structure (57). The inlet lip (52) extends circumferentially about an axial centerline (24). The bulkhead (56) extends circumferentially about the axial centerline (24). The bulkhead (56) is configured with the inlet lip (52) to form a cavity (90) axially between the inlet lip (52) and the bulkhead (56). The reinforcement structure (57) extends circumferentially about the axial centerline (24). The reinforcement structure (57) is connected to and extends axially between the inlet lip (52) and the bulkhead (56) thereby radially dividing the cavity (90) into an inner sub-cavity (90B) and an outer sub-cavity (90A).


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    Titel :

    NACELLE INLET WITH REINFORCEMENT STRUCTURE


    Weitere Titelangaben:

    GONDELEINLASS MIT VERSTÄRKUNGSSTRUKTUR
    ENTRÉE DE NACELLE À STRUCTURE RENFORCÉE


    Beteiligte:

    Erscheinungsdatum :

    20.04.2022


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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