An aircraft gas turbine engine includes an engine core including a turbine, a compressor, a core shaft connecting the turbine to compressor, and a core casing surrounding the engine core. A fan is located upstream of the engine core and fan casing surrounds the fan. A gearbox receives input from the core shaft and outputs drive to rotate the fan. A single plane support structure connects the core and fan casing. The support structure includes an inner ring, outer ring and plurality of circumferentially spaced radially extending struts connecting the inner and outer ring. The inner ring including a torsion box and a gearbox and fan support structure is connected to the torsion box. A front and rear mount are configured to connect the gas turbine engine to the aircraft, wherein the front mount is coupled to the torque box and the rear mount is coupled to the core casing.


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    Title :

    GEARED TURBOFAN GAS TURBINE ENGINE MOUNTING ARRANGEMENT


    Contributors:

    Publication date :

    2020-01-30


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    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 / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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