An aircraft gas turbine engine 100 comprises a fan 130, a compressor 160, a turbine 180, and an exhaust module. The engine comprises a first and second engine mount plane 240, 250. The first and second engine mount planes support the engine in a machine body (282, figure 18). The engine has an axial length L. The first engine mount plane is positioned axially along the engine at a first engine mount plane position 241 being within a range of between 0.24*L to 0.32*L from an inlet face 116 of the engine. The second engine mount plane is positioned axially along the engine at a second engine mount plane position 251 being within a range of between 0.73*L to 0.79*L from the inlet face. Providing the gas turbine engine with a first engine mount plane part-way along the length of the engine, and a second engine mount plane at a rear portion of the engine, makes the process of installing the engine into the machine body easier and more convenient.


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    Titel :

    An improved gas turbine engine


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

    Erscheinungsdatum :

    2023-03-15


    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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