A gas turbine engine for an aircraft comprising an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan comprising a plurality of fan blades; a gearbox that receives an input from the core shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the core shaft, and a front mount and a rear mount, the front and rear mounts being configured to connect the gas turbine engine to the aircraft, wherein the front mount is coupled to a casing 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.
Geared Turbofan Engine Mount Arrangement
2019-10-03
Patent
Elektronische Ressource
Englisch
Geared turbofan gas turbine engine mounting arrangement
Europäisches Patentamt | 2021
|GEARED TURBOFAN GAS TURBINE ENGINE MOUNTING ARRANGEMENT
Europäisches Patentamt | 2020
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