An assembly (54) is provided for an aircraft propulsion system (20). This assembly (54) 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 (120). The inlet lip (62) forms a leading edge (78) 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 (120) includes an exterior skin (122), a mount (124) and an electric heater (126) configured to heat the exterior skin (122). The exterior skin (122) forms a respective circumferential section of the inlet lip (62) and a respective circumferential section of the outer barrel (60). The mount (148) is bonded to the exterior skin (122) and mechanically attached to the inner barrel (58).
SEGMENTED NACELLE INLET LIP WITH ELECTRIC ANTI-ICING SYSTEM
SEGMENTIERTE GONDELEINLASSLIPPE MIT ELEKTRISCHEM ENTEISUNGSSYSTEM
LÈVRE D'ENTRÉE DE NACELLE SEGMENTÉE AVEC SYSTÈME D'ANTIGIVRAGE ÉLECTRIQUE
2025-02-12
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
Segmented nacelle inlet lip with electric anti-icing system
European Patent Office | 2025
|SEGMENTED NACELLE INLET LIP WITH ELECTRIC ANTI-ICING SYSTEM
European Patent Office | 2025
|SEGMENTED NACELLE INLET LIP WITH ELECTRIC ANTI-ICING SYSTEM
European Patent Office | 2025
|SEGMENTED NACELLE INLET LIP WITH ELECTRIC ANTI-ICING SYSTEM
European Patent Office | 2025
|SEGMENTED NACELLE INLET LIP WITH ELECTRIC ANTI-ICING SYSTEM
European Patent Office | 2025
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