A gas turbine engine comprises, in axial flow sequence, a fan assembly, a compressor module, a turbine module, and an exhaust module. The gas turbine engine comprises first and second engine mount planes. The first and second engine mount planes are configured to support gas turbine engine in machine body. The gas turbine engine has axial length L, with axial length extending from inlet face of engine to exhaust face of engine. The first engine mount plane is positioned axially along gas turbine engine at first engine mount plane position, with first engine mount plane position within a range of between 0.24*L to 0.32*L from the inlet face of the engine. The second engine mount plane is positioned axially along gas turbine engine at second engine mount plane position, with second engine mount plane position within a range of between 0.73*L to 0.79*L from the inlet face of the engine.


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    Titel :

    IMPROVED GAS TURBINE ENGINE


    Beteiligte:
    GALLAGHER JAMIE W (Autor:in) / BLACKER DANIEL (Autor:in) / BLAKEMORE HUGH J (Autor:in) / MANSER ADRIAN M (Autor:in) / WATSON JONATHAN V (Autor:in) / FRY ALEXANDER L (Autor:in) / BARKER ROBERT A (Autor:in) / THORP JAMES (Autor:in) / PARENT MARIE-OCÉANE (Autor:in)

    Erscheinungsdatum :

    2023-06-01


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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