公开(公告)号：US10968835B2

公开(公告)日：2021-04-06

申请号：US16437907

申请日：2019-06-11

Applicant: ROLLS-ROYCE plc

Inventor： Alan R. Maguire ,  Richard G. Stretton

IPC: F02C7/00 ,  F02C9/22 ,  F02C7/36

Abstract: Apparatus for a gas turbine engine, the apparatus comprising: a core engine casing having a longitudinal axis and including: an inner wall defining at least part of a core airflow path through the gas turbine engine; an outer wall defining an external surface of the core engine casing, a first cavity being defined between the inner wall and the outer wall of the core engine casing; a plurality of guide vanes extending radially from the outer wall of the core engine casing; a torque box defined within the first cavity of the core engine casing and at least partially overlapping axially with the plurality of guide vanes, the torque box defining a second cavity; and an accessory gear box positioned within the second cavity of the torque box.

公开(公告)号：US10995678B2

公开(公告)日：2021-05-04

申请号：US16044869

申请日：2018-07-25

Applicant: ROLLS-ROYCE plc

Inventor： Alan R. Maguire ,  Timothy J. Scanlon ,  Luis F. Llano ,  Paul A. Sellers

IPC: F02C9/18 ,  F01D11/24 ,  F02K3/075 ,  F02C7/18 ,  F01D25/24 ,  F02C3/04 ,  F01D25/12 ,  F02K3/06

Abstract: A gas turbine engine has a core engine including: a compressor, combustion equipment which receives compressed air from the compressor, a circumferential row of nozzle guide vanes, and a turbine. The nozzle guide vanes defines a throat receiving hot working gases from the combustion equipment into the turbine. The gas turbine engine further has an air system which is switchably operable between an on-position which opens a diversion pathway along which a portion of the compressed air exiting the compressor bypasses the combustion equipment to join the hot working gases at re-entry holes located between the nozzle guide vanes and a rotor at the front of the turbine, thereby increasing the semi-dimensional mass flow ω(T30)0.5/(P30) of the core engine at the exit of the compressor, and an off-position which closes the diversion pathway, thereby decreasing the semi-dimensional mass flow of the core engine at the exit of the compressor.

公开(公告)号：US10914240B2

公开(公告)日：2021-02-09

申请号：US16451677

申请日：2019-06-25

Applicant: ROLLS-ROYCE plc

Inventor： Alan R. Maguire ,  Geoffrey Hughes

IPC: F02C7/36 ,  F01D25/16 ,  F01D25/34 ,  F02K3/06 ,  F16H1/28 ,  F16H57/08 ,  F01D15/12

Abstract: A gas turbine engine, in particular an aircraft engine, includes: a turbine connected via an input shaft device to a gearbox device having a sun gear, a planet carrier having a plurality of planet gears attached thereto, and a ring gear, the sun gear is connected to the input shaft device, the planet carrier or the ring gear is connected to a propulsive fan via an output shaft device of the gearbox device, with a rear carrier bearing device radially between the planet carrier and a static structure on the input side of the gearbox device or a front carrier bearing device radially between the planet carrier and a static structure on the output side of the gearbox device.

公开(公告)号：US11572805B2

公开(公告)日：2023-02-07

申请号：US17169624

申请日：2021-02-08

Applicant: ROLLS-ROYCE plc

Inventor： Alan R. Maguire ,  Richard Sharpe ,  Neil J. Davies

IPC: F01D25/20 ,  F02C7/06 ,  F01M1/02

Abstract: A system for supplying lubricant to a component of a gas turbine engine having a fan shaft is provided. The system includes a pump drivably couplable to the fan shaft for pumping lubricant to the component. The pump includes an inlet for receiving lubricant from a lubricant source, an outlet for outputting lubricant to the component and a swashplate movable between at least a first position and a second position. The system also includes a swashplate actuator for actuating the swashplate between the first position and the second position according to whether the fan shaft is rotating in a forward direction or a reverse direction opposite to the forward direction.

公开(公告)号：US11230945B2

公开(公告)日：2022-01-25

申请号：US16720068

申请日：2019-12-19

Applicant: ROLLS-ROYCE plc

Inventor： Alan R. Maguire ,  Stewart T. Thornton ,  Philip C. Bond ,  Glenn A. Knight

IPC: F01D25/16 ,  F02C7/06

Abstract: A gas turbine engine for an aircraft. The gas turbine engine comprises a rotatable shaft defining a rotational axis extending between rearward and forward ends of the gas turbine engine and a compressor drum surrounding, and coupled to, the shaft so as to define an annular gap therebetween. The gas turbine engine further comprises an intermediate case arranged axially rearward of the compressor drum and comprising a bearing support element extending into the annular gap, and a forward bearing mounted between the bearing support element and the shaft proximate a forward end of the compressor drum.

公开(公告)号：US10920672B2

公开(公告)日：2021-02-16

申请号：US16451543

申请日：2019-06-25

Applicant: ROLLS-ROYCE plc

Inventor： Alan R. Maguire

IPC: F01D15/12 ,  F01D25/16 ,  F02C7/36 ,  F01D25/34 ,  F02K3/06 ,  F16H1/28 ,  F16H57/08

Abstract: A gas turbine engine, in particular an aircraft engine, includes: a turbine connected via an input shaft device to a gearbox device having a sun gear, a planet carrier having a plurality of planet gears attached thereto, and a ring gear, the sun gear is connected to the input shaft device, the planet carrier or the ring gear is connected to a propulsive fan via an output shaft device of the gearbox device, with a rear carrier bearing device radially between the planet carrier and a static structure on the input side of the gearbox device, an inter-shaft bearing system being positioned radially between the input shaft device and the planet carrier of the gearbox device. The input shaft device having a high rigidity or the input shaft device having a diaphragm section.