An air inlet section (42) for an enclosure (40) for an aircraft engine (10) is provided that includes an inner barrel panel (48), an outer barrel panel (50), a lipskin (46) and a forward bulkhead (52). The lipskin (46) extends between an inner barrel end (58) and an outer barrel end (60). The inner barrel end (58) is disposed proximate the forward end (68) of the inner barrel panel (48) and the outer barrel end (60) is disposed proximate the forward end (68) of the outer barrel panel (50). The forward bulkhead (52) has a panel (74) that extends between an outer radial end (76) and an inner radial end (78). The inner barrel panel (48), the outer barrel panel (50), and the lipskin (46) define an interior annular region (66), and the forward bulkhead (52) defines a sub-portion of interior annular region (66). The outer radial end (76) of the forward bulkhead panel (74) is disposed forward of the inner radial end (78) of the forward bulkhead panel (74).


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    Titel :

    ENGINE ENCLOSURE AIR INLET SECTION


    Weitere Titelangaben:

    MOTORGEHÄUSE LUFTEINLASSBEREICH
    SECTION D'ENTRÉE D'AIR DE CARTER MOTEUR


    Beteiligte:
    CHEN JASON K (Autor:in) / ANDELSON PHILLIP (Autor:in)

    Erscheinungsdatum :

    05.10.2022


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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