A gas turbine engine (10) for an aircraft comprising:an engine core (11) comprising a turbine (19), a compressor (14), and a core shaft (26) connecting the turbine to the compressor;a fan (23) located upstream of the engine core, the fan comprising a plurality of fan blades;a gearbox (30) that receives an input from the core shaft (26) and outputs drive to the fan so as to drive the fan at a lower rotational speed than the core shaft, anda front mount (50) and a rear mount (60), the front and rear mounts being configured to connect the gas turbine engine to the aircraft,wherein the front mount (50) is coupled to a casing (13) of the engine core and the front mount is located at substantially the same axial position as a centre of gravity (CG) of the gas turbine engine or forward of the centre of gravity of the gas turbine engine.


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    Titel :

    A geared turbofan engine mount arrangement


    Erscheinungsdatum :

    09.05.2018


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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