A gas turbine engine with a geared turbofan arrangement with a gearbox in a drive train driven by a turbine, a driving side of the gearbox being driveably connected with a propulsive fan, is provided. The gas turbine includes at least one form locking connection device in a drive train enabling a controlled disengagement of at least one engine part from the drive train in case of a mechanical failure of the gas turbine engine or a part thereof and wherein the at least one form locking connection device is positioned in a torque carrying shaft or a torque carrying part of a shaft and/or wherein the at least one form locking connection device is positioned between the torque bearing coupling of the gearbox with the fan shaft and a torque carrier of the gearbox and at least one load stop for bearing an essential axial load.


    Access

    Download


    Export, share and cite



    Title :

    GAS TURBINE ENGINE WITH A GEARED TURBOFAN ARRANGEMENT


    Contributors:

    Publication date :

    2018-03-22


    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 / F02K JET-PROPULSION PLANTS , Strahltriebwerke



    GEARED TURBOFAN GAS TURBINE ENGINE MOUNTING ARRANGEMENT

    SWIFT ANDREW | European Patent Office | 2020

    Free access

    Geared turbofan gas turbine engine mounting arrangement

    SWIFT ANDREW | European Patent Office | 2021

    Free access

    Gas turbine engine with a geared turbofan arrangement

    BONIFACE DOMINIC | European Patent Office | 2020

    Free access

    Gas turbine engine with a geared turbofan arrangement

    BONIFACE DOMINIC | European Patent Office | 2020

    Free access

    GAS TURBINE ENGINE WITH A GEARED TURBOFAN ARRANGEMENT

    BONIFACE DOMINIC | European Patent Office | 2018

    Free access