An assembly (54) is provided for an aircraft propulsion system. This assembly (54) includes a nacelle inlet structure (34) extending axially along and circumferentially about an axis (28). The nacelle inlet structure (34) includes an inlet lip (62), an inner barrel (58), an outer barrel (60) and a plurality of supports (66, 142A). The inlet lip (62) forms a leading edge (86) of the nacelle inlet structure (34). The inner barrel (58) projects axially aft away from the inlet lip (62). The outer barrel (60) projects axially aft away from the inlet lip (62). The outer barrel (60) is radially outboard of and axially overlaps the inner barrel (58). The supports (66, 142A) are arranged circumferentially about the axis (28) in an array. Each of the supports (66, 142A) extends longitudinally along the axis (28). Each of the supports (66, 142A) extends radially between and is connected to the inner barrel (58) and the outer barrel (60).


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    Titel :

    OUTER BARREL SUPPORT STRUCTURE FOR NACELLE INLET STRUCTURE


    Weitere Titelangaben:

    AUSSENZYLINDERSTÜTZSTRUKTUR FÜR GONDELEINLASSSTRUKTUR
    STRUCTURE DE SUPPORT DE TUBE EXTERNE POUR STRUCTURE D'ENTRÉE DE NACELLE


    Beteiligte:
    MINER JASEN A (Autor:in)

    Erscheinungsdatum :

    12.02.2025


    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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