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.

公开(公告)号：US12209536B2

公开(公告)日：2025-01-28

申请号：US18609514

申请日：2024-03-19

Applicant: ROLLS-ROYCE plc

Inventor： Nicholas Grech ,  Matthew J. Willshee ,  Jacopo Tacconi

IPC: F02C7/224 ,  B64D37/30 ,  B64D37/34 ,  F02C3/22

Abstract: A propulsive aircraft gas turbine engine comprises a turbine disposed in a gas turbine engine core flow and a recuperator heat exchanger disposed downstream of the turbine in gas turbine engine core flow, the recuperator heat exchanger being configured to transfer heat from the gas turbine engine core flow to gas turbine engine fuel. The recuperator heat exchanger is configured to accommodate a portion of the gas turbine engine core flow therethrough, the remainder being bypassed around the recuperator heat exchanger.

公开(公告)号：US11698023B2

公开(公告)日：2023-07-11

申请号：US17245163

申请日：2021-04-30

Applicant: ROLLS-ROYCE plc

Inventor： Matthew J. Willshee

IPC: F02C6/20 ,  B64D13/02 ,  F02C7/275 ,  B64D13/06 ,  F16D41/12 ,  F16H57/037

CPC classification number: F02C6/20 ,  B64D13/02 ,  F02C7/275 ,  B64D2013/0644 ,  B64D2013/0696 ,  F05D2220/323 ,  F05D2260/40311 ,  F16D41/12 ,  F16H57/037

Abstract: An aircraft cabin blower system comprises a cabin blower including a compressor configured to provide air to a cabin of the aircraft; a variable drive system configured to drive the compressor and including an electric variator and a summing gearbox; and a main transmission configured, when operating in a blower mode, to receive mechanical power from a gas turbine engine and input mechanical power to the summing gearbox in a forward direction; and configured, when operating in a starter mode, to receive mechanical power from the summing gearbox and input mechanical power to the gas turbine engine. The aircraft cabin blower system further includes a first one-way rotation device adapted to permit free rotation of the main transmission in the forward direction and to prevent rotation of the main transmission in a reverse direction opposite to the forward direction.