An assembly (54) for an aircraft propulsion system (20) includes a first lip segment (92) and a second lip segment (92). The first lip segment (92) includes a first lip skin (96), a first mount (98A) and a first electric heater (100). The first mount (98A) is disposed at a first side (94A) of the first lip segment (92) and connected to the first lip skin (96). The first electric heater (100) is disposed at the first side (94A) of the first lip segment (92) and integrated with the first lip skin (96). The second lip segment (92) includes a second lip skin (96), a second mount (98B) and a second electric heater (100). The second mount (98B) is disposed at a second side (94B) of the second lip segment (92) and connected to the second lip skin (96). The second mount (98B) is removably attached to the first mount (98A). The second electric heater (100) is disposed at the second side (94B) of the second lip segment (92) and integrated with the second lip skin (96).
SEGMENTED NACELLE INLET LIP WITH ELECTRIC THERMAL ANTI-ICING SYSTEM
SEGMENTIERTE GONDELEINLASSLIPPE MIT ELEKTRISCHEM THERMISCHEM ENTEISUNGSSYSTEM
LÈVRE D'ENTRÉE DE NACELLE SEGMENTÉE AVEC SYSTÈME D'ANTIGIVRAGE THERMIQUE ÉLECTRIQUE
06.11.2024
Patent
Elektronische Ressource
Englisch
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