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
29.11.2022
Patent
Elektronische Ressource
Englisch
GEARED TURBOFAN GAS TURBINE ENGINE MOUNTING ARRANGEMENT
Europäisches Patentamt | 2020
|Geared turbofan gas turbine engine mounting arrangement
Europäisches Patentamt | 2021
|