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).


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    Title :

    SEGMENTED NACELLE INLET LIP WITH ELECTRIC THERMAL ANTI-ICING SYSTEM


    Additional title:

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


    Contributors:

    Publication date :

    2024-11-06


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



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