公开(公告)号：US11512612B2

公开(公告)日：2022-11-29

申请号：US16292416

申请日：2019-03-05

Applicant: ROLLS-ROYCE plc

Inventor： David R. Coles ,  Gavin M. Rowntree ,  Matthew J. Willshee ,  Zubair Ahmed

IPC: F01D25/28 ,  F02C7/20 ,  B64D27/26

Abstract: 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.