An assembly (54) for an aircraft propulsion system (20) includes a nacelle inlet structure (34). The nacelle inlet structure (34) includes an inlet lip (62), an inner barrel (58), an outer barrel (60), a bulkhead (64) and a plurality of structure segments (116). Each of the structure segments (116) includes an exterior skin (118), an inner mount flange (144), an outer mount flange (160) and an electric heater (126) configured to heat the exterior skin (118). The exterior skin (118) forms at least a respective circumferential section of the inlet lip (62). The inner mount flange (144) is connected to and projects radially outward away from the exterior skin (118). An inner fastener (146) extends axially through the inner mount flange (144) and couples the inner mount flange (144) to the inner barrel (58). The outer mount flange (160) is connected to and projects radially inward away from the exterior skin (118). An outer fastener (162) extends axially through the outer mount flange (140) and couples the outer mount flange (140) to the bulkhead (64).
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
2025-03-05
Patent
Electronic Resource
English
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
|