公开(公告)号：US10145387B2

公开(公告)日：2018-12-04

申请号：US15136409

申请日：2016-04-22

Applicant: ROLLS-ROYCE plc

Inventor： Glenn A Knight ,  Alan R Maguire ,  Daniel Robinson ,  George Bostock ,  Mark J Wilson

IPC: F04D29/52 ,  B64D13/06 ,  F04D19/00 ,  F04D27/00 ,  F04D29/32 ,  F04D29/68 ,  B64C21/04 ,  B64D13/02 ,  B64D13/04 ,  F16H15/38 ,  F16H37/08 ,  F04D25/02 ,  F04D27/02 ,  B64D33/02

Abstract: A gas turbine engine comprising a compressor, a compressor case surrounding the compressor and a compressor tip injector system is disclosed. The compressor tip injector system comprises a cabin blower system comprising a cabin blower compressor arranged in use to compress air used in a cabin of an aircraft and by the compressor tip injector system. The compressor case comprises one or more injectors of the compressor tip injector system through which in use air from the cabin blower compressor is injected towards blade tip ends of blades of the compressor as they rotate.

公开(公告)号：US10655475B2

公开(公告)日：2020-05-19

申请号：US15352468

申请日：2016-11-15

Applicant: ROLLS-ROYCE plc

Inventor： Alan R Maguire ,  Timothy J Scanlon

IPC: F01D11/24 ,  F02C7/18 ,  F01D9/04 ,  F01D25/12 ,  F01D25/24 ,  F02C9/18 ,  F01D11/20 ,  F01D11/14 ,  F02C7/12 ,  F01D5/18 ,  F02C3/10 ,  F16K1/22 ,  F23R3/00

Abstract: A gas turbine engine includes a turbine and a turbine cooling arrangement. The turbine includes a turbine rotor surrounded by a static rotor track liner, and a nozzle guide vane downstream of the rotor in a core main gas flow path. The cooling arrangement includes a first air duct that provides cooling airflow to a rotor track liner cooling plenum and a second air duct that provides a cooling airflow to the nozzle guide vane. A common manifold is upstream in the cooling airflow of the ducts and provides cooling air to the ducts. A two-way valve modulates air provided to the ducts from the manifold. The valve is operates in a first or second mode. In the first mode, air flow to the first duct is relatively high and airflow to the second duct is relatively low compared to where the valve is operated in the second mode.

公开(公告)号：US11454174B2

公开(公告)日：2022-09-27

申请号：US17147762

申请日：2021-01-13

Applicant: ROLLS-ROYCE PLC

Inventor： Alan R Maguire

IPC: F02C7/36 ,  F01D25/16 ,  F01D25/34 ,  F02K3/06 ,  F16H1/28 ,  F16H57/08 ,  F01D15/12 ,  F02C3/107 ,  F01D5/02 ,  F02C7/06 ,  F02K3/04

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.

公开(公告)号：US10371059B2

公开(公告)日：2019-08-06

申请号：US14957972

申请日：2015-12-03

Applicant: ROLLS-ROYCE plc

Inventor： Glenn A Knight ,  Alan R Maguire ,  Daniel Robinson

IPC: B64D13/02 ,  B64D13/06 ,  B64D31/14 ,  F02C7/275 ,  F02C7/277 ,  F16H15/38 ,  F16H37/08

Abstract: An aircraft cabin blower system comprising a transmission and a compressor is disclosed. The system has a forward configuration in which the compressor is drivable in use via the transmission. The transmission comprises a toroidal continuously variable transmission giving selectively variable control over the rate at which the compressor is driven.

公开(公告)号：US09845682B2

公开(公告)日：2017-12-19

申请号：US14709883

申请日：2015-05-12

Applicant: ROLLS-ROYCE PLC

Inventor： Alan R Maguire ,  Kenneth F Udall ,  Phillip J Doorbar

IPC: F01D5/32 ,  F01D5/02 ,  F01D5/30 ,  F01D25/16

CPC classification number: F01D5/025 ,  F01D5/3007 ,  F01D25/164 ,  F05D2220/36

Abstract: A fan disc is provided for supporting fan blades of a gas turbine engine. The fan disc has a disc body having axially extending slots for receiving, in use, dovetail root fixings of a circumferential row of fan blades. The fan disc further has an annular drive arm which extends radially inwardly from a forward portion of the disc body to a connector for engaging, in use, with a corresponding connector portion of a drive shaft of the engine. The fan disc further has a hoop stiffening ring which is removably mounted to a rear portion of the disc body, the stiffening ring being axially spaced from the drive arm to increase the torsional stiffness of the fan disc.