An anti-icing system (40) for an aircraft nacelle (12) includes an inner duct (44) and an outer duct (48). The inner duct (44) extends through a first bulkhead (46) between a gas turbine engine (10) and a plenum (38) of the nacelle (12). The inner duct (44) is configured to deliver heated gases from the gas turbine engine (10) to the plenum (38). The outer duct (48) includes a first end (48E1) and a second end (48E2). The outer duct (48) circumferentially encompasses at least a portion of the inner duct (44) on a first side (46S1) of the bulkhead (46). At least one of the first end (48E1) and the second end (48E2) of the outer duct (48) is mounted to at least one of the respective first bulkhead (46) and a second bulkhead (36) by a bellows (50) forming an annular seal between the respective bulkhead (46, 36) and the outer duct (48).


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    Titel :

    ANTI-ICING SYSTEM FOR AN AIRCRAFT NACELLE


    Weitere Titelangaben:

    ENTEISUNGSSYSTEM FÜR EINE FLUGZEUGGONDEL
    SYSTÈME DE DÉGIVRAGE DE NACELLE D'AÉRONEF


    Beteiligte:
    KROEGER DANIEL (Autor:in) / PRETTY MICHAEL S (Autor:in) / RAMLAOUI JIHAD (Autor:in)

    Erscheinungsdatum :

    2022-03-30


    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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