公开(公告)号：US20230120297A1

公开(公告)日：2023-04-20

申请号：US17935269

申请日：2022-09-26

Applicant: ROLLS-ROYCE plc

Inventor： Philip D. BUTLER

IPC: B64D27/10 ,  B64D27/24 ,  B64D33/08 ,  F02C6/00 ,  H01M8/04111 ,  H01M8/04119 ,  H01M8/04082 ,  H02K7/18

Abstract: An aircraft propulsion system comprises a gas turbine engine arranged to provide propulsive thrust and a fuel cell system having an air input port, the aircraft propulsion system being configured such that air from a compressor of the gas turbine engine is provided to the air input port during operation of the aircraft propulsion system. The fuel cell system is able to provide appreciable electrical power at altitude without the need for a dedicated compressor.

公开(公告)号：US11629667B2

公开(公告)日：2023-04-18

申请号：US17193317

申请日：2021-03-05

Applicant: ROLLS-ROYCE PLC

Inventor： Alastair D Moore ,  Robert J Telling

IPC: F02K3/06 ,  F02C7/24

Abstract: A gas turbine engine generates noise during use, and one particularly important flight condition for noise generation is take-off. A gas turbine engine that has high efficiency provides low noise, in particular from the fan and the turbine that drives the fan. Values are defined for a noise parameter NP that results in a gas turbine engine having reduced combined fan and turbine noise.

公开(公告)号：US11629650B2

公开(公告)日：2023-04-18

申请号：US17651918

申请日：2022-02-22

Applicant: ROLLS-ROYCE plc

Inventor： Martin Berthold ,  Colin Young

IPC: F16H57/04 ,  F02C7/36 ,  F16H57/08

Abstract: A planetary gearbox having a sun gear, a plurality of planet gears, a ring gear, and a plurality of journal bearing pins. At its axially forward face side and/or at its axially rearward face side, each planet gear forms a recess that extends inside the planet gear starting from the face side. The planet gear forms a protrusion at its axially forward face side and/or at its axially rearward face side. The protrusion has an axial extent and a radial extent, wherein the radial extent is limited at the respective face side to the area between the planet gear inner bore and the radial inner limit of the respective recess in the planet gear, and wherein the protrusion is configured to provide for a flow path for oil emerging from the journal bearing that guides the oil away from the journal bearing.

公开(公告)号：US20230116266A1

公开(公告)日：2023-04-13

申请号：US18054081

申请日：2022-11-09

Applicant: Rolls-Royce plc

Inventor： Ellis Fui Hen Chong ,  Alexander C. Smith ,  Yuanpeng Zhou

IPC: H02K1/17

Abstract: The present disclosure relates to an electromechanical system comprising a toothed rotor and a stator segment. The stator segment comprises an armature coil defining a coil interior. The stator segment further comprises first and second stator portions, each stator portion comprising connected inner and outer radially extending poles. Each of the inner poles passes through the coil interior and each of the outer poles is provided outside of the coil interior. The stator segment further comprises a bridge spacing the stator portions and the bridge comprises a magnetic field generator arranged to generate a magnetic field between the stator portions.

公开(公告)号：US20230101578A1

公开(公告)日：2023-03-30

申请号：US17941374

申请日：2022-09-09

Applicant: ROLLS-ROYCE PLC

Inventor： Peter SWANN ,  Kevin M BRITCHFORD

IPC: B64D27/10 ,  B64D27/24 ,  B64D31/00 ,  F02C6/00

Abstract: An aircraft hybrid propulsion system (5) comprising an inboard gas turbine engine (10a, 10c) and an outboard gas turbine engine (10b, 10d), each comprising a propulsor (12a, 12b) and a respective electric machine (32a, 32b) coupled to one or more engine shaft (24a, 24b). An electrical interconnection (34) is provided between the electric machine (32a) of the inboard gas turbine engine (10a) and the electric machine (32b) of the outboard gas turbine engine (10b). A controller (36) is configured to transfer electrical power between the inboard gas turbine engine electrical machine and the outboard gas turbine engine electrical machine when a thrust setting change is selected.

公开(公告)号：US20230093834A1

公开(公告)日：2023-03-30

申请号：US17931152

申请日：2022-09-12

Applicant: ROLLS-ROYCE plc

Inventor： Dharun VADUGAPPATTY SRINIVASAN ,  Sridhar IDAPALAPATI

IPC: F01D5/00 ,  F01D5/28 ,  B29C73/10 ,  B29C73/26

Abstract: A method of repairing a composite blade. The composite blade includes a metal work bonded to a composite part through an adhesive layer. The method includes determining a locally damaged portion of the metal work, and removing a bullet portion corresponding to the locally damaged portion. The method further includes detaching, debonding, and removing a first wing portion from the composite part to obtain a first exposed surface portion. The method further includes detaching, debonding, and removing a second wing portion from the composite part to obtain a second exposed surface portion. The method further includes reconditioning the first and second exposed surface portions to obtain first and second reconditioned surface portions, respectively, and applying first and second adhesive layers to the first and second reconditioned surface portions respectively. The method further includes bonding a metal work patch to the first and second adhesive layers.

公开(公告)号：US11603993B2

公开(公告)日：2023-03-14

申请号：US17848798

申请日：2022-06-24

Applicant: ROLLS-ROYCE plc ,  ROLLS-ROYCE DEUTSCHLAND LTD & CO KG

Inventor： Luca Tentorio ,  Imon-Kalyan Bagchi

IPC: F23R3/34 ,  F23R3/14 ,  F02C7/36

Abstract: A lean burn combustor includes a plurality of lean burn fuel injectors, each including a fuel feed arm and a lean burn fuel injector head with a lean burn fuel injector head tip, wherein the lean burn fuel injector head tip has a lean burn fuel injector head tip diameter, the lean burn fuel injector head including a pilot fuel injector and a main fuel injector, the main fuel injector being arranged coaxially and radially outwards of the pilot fuel injector; and a combustor chamber extending along an axial direction for a length and including a radially inner annular wall, a radially outer annular wall, and a meter panel defining the size and shape of the combustor chamber, wherein the combustor chamber includes primary and secondary combustion zones. A ratio of the combustor chamber length to the lean burn fuel injector head tip diameter is less than 5.

公开(公告)号：US20230066032A1

公开(公告)日：2023-03-02

申请号：US17822506

申请日：2022-08-26

Applicant: ROLLS-ROYCE plc

Inventor： Tony L. WIDDOWSON ,  Oliver C. TAYLOR-TIBBOTT

IPC: F01D11/00

Abstract: A seal arrangement configured to provide an airtight and fluid-tight seal between a first component and a second component, having a first pressure boundary seal disposable at least partially within the gap between the first component and the second component, the first pressure boundary seal being fixable to one of the first or second components to create an airtight seal with the other of the first or second component, the seal arrangement also having a first flame deflector that is configured to bridge across and cover the gap between the first component and the second component so as to create a fluid-tight seal over the gap between the first component and the second component, where the first flame deflector has a convex external shape so as to prevent any fluid impinging upon the first flame deflector from pooling on the first pressure boundary seal.

公开(公告)号：US11585278B1

公开(公告)日：2023-02-21

申请号：US17853144

申请日：2022-06-29

Applicant: ROLLS-ROYCE plc

Inventor： Peter Swann ,  David M Beaven ,  Craig W Bemment ,  Alastair G Hobday ,  Benjamin J Keeler ,  Christopher P Madden ,  Martin K Yates

IPC: G01N21/35 ,  F02C9/00 ,  B64D27/10 ,  B64D47/00 ,  G01N33/28 ,  G01N21/64 ,  G01N21/33 ,  G01N21/3577 ,  B64D37/00

Abstract: A method of determining one or more fuel characteristics of an aviation fuel for powering a gas turbine engine of an aircraft includes: measuring one or more trace substance parameters of the fuel, the one or more trace substance parameters each associated with a respective trace substance in the fuel; and determining one or more fuel characteristics of the fuel based on the one or more trace substance parameters. Further, a fuel characteristic determination system, a method of operating an aircraft, and an aircraft.

公开(公告)号：US20230044167A1

公开(公告)日：2023-02-09

申请号：US17814019

申请日：2022-07-21

Applicant: ROLLS-ROYCE plc

Inventor： Fiona HALLIDAY ,  Mark SPRUCE

IPC: F16H57/08 ,  F16C17/02

Abstract: A journal bearing comprising a first component and a second component, the first and second components being arranged to rotate relative to one another in normal use. The first component comprises a first body, a first layer forming a functional surface facing the second component, and a first subsurface layer between the body and the layer. The first subsurface layer is formed of a material having a first coefficient of thermal expansion in the radial direction, and the first body is formed of a material having a second coefficient of thermal expansion in the radial direction. The first coefficient of thermal expansion is lower than the second coefficient of thermal expansion.