Rolls-royce Corporation

Gavin M Rowntree

Ingo H J Jahn

Matthew John Willshee

David Coles

Zubair Ahmed

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

An intershaft seal for inner and outer coaxial shafts which rotate relative to each other. The seal is located in an annular space between the shafts and maintains an axial pressure differential between a fluid pressure on the first side of the seal and a fluid pressure on the other, second side of the seal. The seal comprises a sealing ring which is coaxial with the shafts and which forms a sealing contact with the outer shaft to maintain the pressure differential.

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Derby, United Kingdom

Gavin M Rowntree