A method is provided for disassembling a gas turbine engine (20). The gas turbine engine (20) includes a compressor section (29), a combustor section (30), a turbine section (31), a static structure (36) and a bypass duct (40). The static structure (36) houses and supports the compressor section (29), the combustor section (30) and the turbine section (31). The static structure (36) includes a turbine support structure (46). The bypass duct (40) includes an inner duct wall (80), an outer duct wall (82) and a bypass flowpath (84) formed radially between the inner duct wall (80) and the outer duct wall (82). The outer duct wall (82) extends axially along the static structure (36) and overlaps the turbine support structure (46). During the method, the turbine support structure (46) is removed from the gas turbine engine (20) while the outer duct wall (82) remains installed.


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    Titel :

    GAS TURBINE ENGINE DISASSEMBLY/ASSEMBLY METHODS


    Weitere Titelangaben:

    GASTURBINENTRIEBWERKS-ZERLEGUNGS-/-MONTAGEVERFAHREN
    PROCÉDÉS D'ASSEMBLAGE/DÉSASSEMBLAGE DE TURBINE À GAZ


    Beteiligte:
    PORCO CARLO S (Autor:in) / HENRIKSEN GEOFFREY (Autor:in) / WEDEMIRE JASON (Autor:in) / MATHIAS ANTHONY (Autor:in) / HUNZE MICHAEL (Autor:in) / LAVOIE LOUIS (Autor:in) / PAYNTER MARVEN (Autor:in) / WILKINSON DENNIS (Autor:in)

    Erscheinungsdatum :

    01.03.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT




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