公开(公告)号：US10793279B2

公开(公告)日：2020-10-06

申请号：US16238841

申请日：2019-01-03

Applicant: ROLLS-ROYCE PLC

Inventor： Richard Sharpe ,  Glenn A Knight

IPC: B64D13/02 ,  F02C7/32 ,  B64D41/00 ,  F01D15/10 ,  F02C7/275 ,  F04D13/02 ,  F04D27/00 ,  F04D29/05

Abstract: An aircraft cabin blower system includes: a transmission configured to receive mechanical power from a first part of a gas turbine engine in the form of a first transmission input; and an electrical circuit including a first electrical machine, a second electrical machine, and a power management system, wherein an output of the transmission is configured to drive a cabin blower compressor when operating in a blower mode, the first electrical machine being configured to receive mechanical power from a second part of the gas turbine engine and act as a generator to provide electrical power to the power management system, and the second electrical machine being configured to act as a motor providing mechanical power to the transmission in the form of a second transmission input, the second electrical machine being driven by electrical power from the power management system.

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：US11084591B2

公开(公告)日：2021-08-10

申请号：US16239338

申请日：2019-01-03

Applicant: ROLLS-ROYCE plc

Inventor： Glenn A Knight ,  Richard Sharpe

IPC: B64D13/02 ,  F01D15/10 ,  F02C7/26 ,  F02C7/32 ,  F04D25/06 ,  F16H1/28 ,  B64D13/04 ,  F16H3/08

Abstract: An aircraft cabin blower system includes a transmission configured to receive mechanical power from a gas turbine engine in the form of a first transmission input; and an electrical circuit including a first electrical machine, a second electrical machine, and power management system, wherein, when operating in a blower mode, the first electrical receives mechanical power from the gas turbine engine and act as a generator to provide electrical power to the power management system, and the second electrical machine acts as a motor providing mechanical power to the transmission in the form of a second transmission input, the second electrical machine being driven by electrical power from the power management system. The transmission's output drives a cabin blower compressor when operating in the blower mode, a speed of the output of the transmission being determined by a function of a speed of the first and second transmission inputs.

公开(公告)号：US10605107B2

公开(公告)日：2020-03-31

申请号：US15620024

申请日：2017-06-12

Applicant: ROLLS-ROYCE PLC

Inventor： Marko Bacic ,  Glenn A Knight

IPC: F01D11/20 ,  B64D27/10 ,  F02C7/18 ,  F01D11/24 ,  B64D13/02 ,  B64D13/08 ,  B64D27/16 ,  F02C6/08 ,  B64D13/00 ,  B64D13/06

Abstract: A gas turbine engine is disclosed having a tip clearance control system. The tip clearance control system has a cabin blower system, a casing arranged in use about a rotor of a gas turbine engine and a fluid delivery passage. The cabin blower system having a cabin blower compressor arranged in use to compress fluid used in a cabin of an aircraft and to compress fluid conducted via the fluid delivery passage into heat exchange with the casing.

公开(公告)号：US10393068B2

公开(公告)日：2019-08-27

申请号：US15262612

申请日：2016-09-12

Applicant: ROLLS-ROYCE plc

Inventor： Andrew Swift ,  Stewart T Thornton ,  Paul Simms ,  Glenn A Knight

IPC: F02K3/06 ,  F01D25/16 ,  F02C3/107 ,  F02C7/06 ,  F02C7/36

Abstract: A gas turbine engine, including: a low pressure spool having a low pressure compressor and a low pressure turbine connected by a low pressure shaft; a reduction gear train having a sun gear, a carrier having a plurality of planet gears attached thereto, and a ring gear, wherein one of the sun gear, carrier or ring gear is connected to the low pressure shaft, and another of the sun gear, carrier and ring gear provides an output drive; a propulsive fan mounted fore of the gear train; a fan shafting arrangement comprising a fan shaft which is connected to the output drive of the gear train and a fan support shaft which passes through center of the gear train along the axis of rotation of the gearbox and fan, wherein the fan shafting arrangement is rotatably supported by at least two axially separated bearings.

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.