An assembly (54) for an aircraft propulsion system (20) includes a nacelle inlet structure (34) which extends axially along and circumferentially around a centerline (28). The nacelle inlet structure (34) includes an inlet lip (62), an inner barrel (58), an outer barrel (60) and a plurality of structure segments (160). 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). Each of the structure segments (160) includes an exterior skin (162), a mount (164) and an electric heater (166) configured to heat the exterior skin (162). The exterior skin (162) forms a respective circumferential section of the inlet lip (62). The mount (164) is connected to the exterior skin (162). A fastener (190) extends radially through the mount (164) and attaches a respective one of the structure segments (160) to the inner barrel (58).


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    Titel :

    SEGMENTED NACELLE INLET LIP WITH ELECTRIC ANTI-ICING SYSTEM


    Weitere Titelangaben:

    SEGMENTIERTE GONDELEINLASSLIPPE MIT ELEKTRISCHEM ENTEISUNGSSYSTEM
    LÈVRE D'ENTRÉE DE NACELLE SEGMENTÉE AVEC SYSTÈME D'ANTIGIVRAGE ÉLECTRIQUE


    Beteiligte:

    Erscheinungsdatum :

    12.02.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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