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


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    Title :

    AN IMPROVED GAS TURBINE ENGINE


    Additional title:

    VERBESSERTES GASTURBINENTRIEBWERK
    MOTEUR À TURBINE À GAZ AMÉLIORÉ


    Contributors:

    Publication date :

    2023-03-15


    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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