公开(公告)号：US20230134139A1

公开(公告)日：2023-05-04

申请号：US18050825

申请日：2022-10-28

Applicant: ROLLS-ROYCE plc

Inventor： Damian MARTIN ,  James E. CLISSOLD

IPC: F23R3/28 ,  F02C7/28

Abstract: A combustor arrangement includes a fuel injector, and a seal arranged around the fuel injector and having an upstream end and a downstream end. The seal includes an annular body at least partially abutting the fuel injector. The annular body includes an inner surface facing the fuel injector and an outer surface radially spaced apart from the inner surface relative to the central axis. The annular body further includes a plurality of slots disposed on the inner surface and circumferentially spaced apart from each other relative to the central axis. Each slot axially extends at least partially from the downstream end to the upstream end. Each slot is disposed in fluid contact with the fuel injector. The seal also includes a flange radially extending from the outer surface of the annular body at the upstream end.

公开(公告)号：US20230132101A1

公开(公告)日：2023-04-27

申请号：US18045857

申请日：2022-10-12

Applicant: ROLLS-ROYCE plc

Inventor： Christopher A MURRAY

IPC: B64D13/06 ,  F02C7/36 ,  F02C7/32

Abstract: A cabin blower system, for an aircraft, comprising: a cabin blower compressor, for compressing air for delivery to a cabin of an aircraft, comprising a compressor drive shaft running on a contactless bearing system; and a transmission comprising an input and an output, the input being arranged to receive power from an engine of the aircraft and the output being arranged to mechanically drive the cabin blower compressor, wherein the output of the transmission is mechanically coupled with the compressor drive shaft via a flexible drive coupling.

公开(公告)号：US20230125918A1

公开(公告)日：2023-04-27

申请号：US17973609

申请日：2022-10-26

Applicant: Rolls-Royce Deutschland Ltd & Co KG ,  Rolls-Royce plc

Inventor： Matthew THOMSON ,  Romek OTT ,  Igor SIKORSKI ,  Sabina HEYEN

IPC: F02C7/18 ,  F23R3/04 ,  F23R3/16 ,  F23R3/42

Abstract: A combustion chamber assembly includes a through hole on the combustion chamber wall bounded on an outer side of the wall by a hole edge and a combustion chamber shingle having a collar bounding a mixing air hole on the outer side of the wall and protruding with a first collar portion beyond the hole edge on the outer side of the wall. A cooling air opening is formed on an inner circumferential surface of a duct portion of the mixing air hole adjoining the first collar portion and extending in the direction of a combustion space, the cooling air opening leading into a cooling air duct which extends through the duct portion and via which cooling air is guided out of the mixing air hole in a direction of a hot side of the shingle facing the combustion space.

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.