公开(公告)号：US20240077022A1

公开(公告)日：2024-03-07

申请号：US18233533

申请日：2023-08-14

Applicant: ROLLS-ROYCE plc

Inventor： Paul R. DAVIES ,  David A. JONES ,  Richard G. MOCHRIE

IPC: F02C7/16 ,  B64D27/10

CPC classification number: F02C7/16 ,  B64D27/10 ,  F05D2260/232

Abstract: A thermal management system for an aircraft comprises a first gas turbine engine, one or more first electric machines rotatably coupled to the first gas turbine engine, a first thermal bus, a first heat exchanger, and one or more first ancillary systems. The first thermal bus comprises a first heat transfer fluid, with the first heat transfer fluid being in fluid communication, in a closed loop flow sequence, between the or each first electric machine, the first gas turbine engine, the first heat exchanger, and the or each first ancillary system. Waste heat energy generated by at least one of the first gas turbine engine, the or each first electric machine, and the or each first ancillary system, is transferred to the first heat transfer fluid. The first heat exchanger is configured to transfer the waste heat energy from the first heat transfer fluid to a dissipation medium.

公开(公告)号：US11920540B2

公开(公告)日：2024-03-05

申请号：US17940034

申请日：2022-09-08

Applicant: ROLLS-ROYCE plc

Inventor： Benjamin J Sellers ,  Stephen J Bradbrook ,  Robert J Corin ,  Richard J Hunsley

IPC: F02K3/06 ,  F01D15/10

CPC classification number: F02K3/06 ,  F01D15/10 ,  F05D2220/323 ,  F05D2220/36

Abstract: An aircraft turbofan gas turbine engine includes a fan assembly, a compressor module, and a turbine module. An electric machine is positioned downstream of the fan assembly and is connected to the turbine module. The fan assembly includes a highest pressure fan stage having a plurality of fan blades defining a fan diameter. The turbine module includes a lowest pressure turbine stage having a row of rotor blades. The gas turbine engine has a fan tip axis that joins a radially outer tip of the leading edge of one of the plurality of fan blades of the highest pressure fan stage, and the radially outer tip of the trailing edge of one of the rotor blades of the lowest pressure turbine stage. The fan tip axis lies in a longitudinal plane which contains a centreline of the gas turbine engine. The fan axis angle is between 11 and 20 degrees.

公开(公告)号：US11905892B2

公开(公告)日：2024-02-20

申请号：US17101932

申请日：2020-11-23

Applicant: ROLLS-ROYCE plc

Inventor： Vasileios Pachidis ,  Luis E Ferrer-Vidal Espana-Heredia

IPC: F04D27/00 ,  F02C9/16 ,  F01D21/00 ,  G06F30/20

CPC classification number: F02C9/16 ,  F01D21/003 ,  F04D27/001 ,  G06F30/20 ,  F05D2260/81 ,  F05D2270/304 ,  F05D2270/3015 ,  F05D2270/3061 ,  F05D2270/44

Abstract: A method of determining performance characteristics of a flow machine having a rotor interacting with a flow field. The method comprises: receiving performance data for the flow machine comprising data values of a performance parameter of the rotor and mass flow for the flow machine at one or more defined rotor condition, the performance data defining a two-dimensional array of data in which points for a common rotor condition are identifiable; determining or receiving exit mass flow values for the flow downstream of the rotor; and identifying one or more point in the received performance data and interpolating from said one or more point to a corresponding one or more point at a different rotor condition based on a correlation of the exit mass flow values for said points.

公开(公告)号：US11904427B2

公开(公告)日：2024-02-20

申请号：US16712782

申请日：2019-12-12

Applicant: ROLLS-ROYCE plc

Inventor： Donka Novovic ,  Dragos A Axinte ,  Alessio Spampinato

IPC: B24B19/00 ,  B24B53/017 ,  B24B53/06 ,  B24B53/14 ,  B24D5/06 ,  B24D18/00

CPC classification number: B24B19/009 ,  B24B53/017 ,  B24B53/06 ,  B24B53/14 ,  B24D5/06 ,  B24D18/0009 ,  B24D2203/00

Abstract: A method of manufacturing a rotary abrasive machining tool, the rotary abrasive machining tool including a hub and a plurality of abrasive segments mounted to the hub, the method including the steps of: mounting each abrasive segment on the hub; machining an abrading edge on each abrasive segment while the abrasive segment is mounted on the hub.

公开(公告)号：US11891184B2

公开(公告)日：2024-02-06

申请号：US17098758

申请日：2020-11-16

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

Inventor： Gideon Daniel Venter ,  Giles E Harvey

IPC: B64D27/02 ,  B64D27/10 ,  B64D27/24 ,  F02C6/20 ,  F02C7/36 ,  H02K7/108 ,  H02K7/116 ,  H02K7/18 ,  H02K7/20 ,  H02K11/00 ,  F16D7/00 ,  F16H57/02

CPC classification number: B64D27/02 ,  B64D27/10 ,  B64D27/24 ,  F02C6/20 ,  F02C7/36 ,  H02K7/108 ,  H02K7/116 ,  H02K7/1823 ,  H02K7/20 ,  H02K11/0094 ,  B64D2027/026 ,  F05D2220/323 ,  F05D2220/76 ,  F16D7/007 ,  F16H57/02 ,  F16H2057/02043

Abstract: An aircraft hybrid propulsion system (5) comprises an internal combustion engine (10) comprising a main drive shaft (24), an electric machine (28) comprising an electric machine rotor (78), a propulsor (12) mounted to a propulsor shaft (62), and a clutch arrangement configured to selectively couple each of the gas turbine engine main drive shaft (24) and electric machine rotor (78) to the propulsor drive shaft (62). The electric machine rotor (78) is mounted coaxially with the main drive shaft (24) and the clutch arrangement comprises a first overrunning clutch (52) configured to couple the main drive shaft (24) to the propulsor drive shaft (62), and a second overrunning clutch (54) configured to couple the electric machine rotor (78) to the propulsor drive shaft (62).

公开(公告)号：US20240035210A1

公开(公告)日：2024-02-01

申请号：US18220922

申请日：2023-07-12

Applicant: ROLLS-ROYCE plc

Inventor： Christopher D. JONES ,  Adam J. BISHOP ,  Richard HALL ,  Ian BUCK ,  Sarvesh DHIMAN

IPC: D03D11/00 ,  B29C70/24

CPC classification number: D03D11/00 ,  B29C70/24 ,  D10B2505/02

Abstract: A method for manufacturing a composite component, including: weaving a multi-layer woven preform from warp and weft tows of fibre-reinforcement material, the woven preform includes: multi-layer weave including: plurality of weft tow layers; plurality of laterally-adjacent stacks extending along the longitudinal direction, primary portion having longitudinal extent along woven preform, the primary portion having one or more edge regions each defining respective lateral side of primary portion; wherein for the or each edge region: the multi-layer weave defines at least the edge region; plurality of stacks in the edge region are binding stacks in which one or more warp tows are interlaced to bind a respective plurality of weft tow layers; weave property differs between binding stacks in the edge region to reduce a thickness of the edge region towards respective lateral side. Also disclosed herein is a woven structure, formed by warp and weft tows of fibre reinforcement material.

公开(公告)号：US11884405B2

公开(公告)日：2024-01-30

申请号：US16683819

申请日：2019-11-14

Applicant: ROLLS-ROYCE plc

Inventor： Geoffrey B Jones ,  Edward J Spalton ,  Steven P Culwick

IPC: B64D15/22 ,  F01D17/08 ,  F02C7/047

CPC classification number: B64D15/22 ,  F01D17/085 ,  F02C7/047 ,  F05D2270/303

Abstract: An apparatus for the detection of either or both of water and ice within a system, more specifically, but not exclusively, the detection of either or both of water or ice crystal ingestion, or ice accretion on an aerofoil, within a gas turbine engine. The apparatus and method compares the measured temperature of the first region with a second temperature value, measured at a distinct second region of the aerofoil, wherein the second radial position of the second sensor is radially offset from the first radial position of the first sensor.

公开(公告)号：US11883927B2

公开(公告)日：2024-01-30

申请号：US17220318

申请日：2021-04-01

Applicant: ROLLS-ROYCE plc

Inventor： Karl S. Huckerby

IPC: B24B51/00 ,  B24B7/10 ,  G05B15/02 ,  G05B19/4097

CPC classification number: B24B51/00 ,  B24B7/10 ,  G05B19/4097 ,  G05B15/02 ,  G05B2219/32228 ,  G05B2219/37047 ,  G05B2219/45147

Abstract: A method of machining a surface of a component. The method comprises scanning the surface of the component to obtain scanned electronic 3D data representing the scanned surface of the component locating a surface defect of the scanned surface and identifying a defect region that surrounds and includes the surface defect, and providing electronic 3D data representing a patch having the desired shape of the defect region. The method also comprises transforming the patch to generate a tooling path for repairing the surface defect. The transformation comprising translating a plurality of nodes of the patch. The translation distance of each node based on the distance of that node from an origin node of the patch. The method further comprises machining the surface of the component according to the generated tooling path.

公开(公告)号：US20240025131A1

公开(公告)日：2024-01-25

申请号：US18220932

申请日：2023-07-12

Applicant: ROLLS-ROYCE PLC

Inventor： Christopher D. JONES ,  Robert C. BACKHOUSE ,  Adam J. BISHOP ,  Ian BUCK ,  Sarvesh DHIMAN

IPC: B29C70/22

CPC classification number: B29C70/222 ,  B29L2031/3076

Abstract: A woven composite component for an aerospace structure or machine, comprising: a compound member extending from a junction with a feeder member, a noodle element extending in a weft direction through the junction. The feeder member comprises first and second feeder portions either side of the junction, each feeder portion comprising warp tows extending towards the junction. There is a compound set of warp tows extending from the first and second feeder portions, each turning at the junction to define warp tows for the compound member. There is a crossing set of warp tows belonging to the compound set, the crossing set comprising warp tows from the first feeder portion and warp tows from the second portion which cross each other at the junction to pass around the noodle element. There is also disclosed a method of manufacturing a preform for a woven composite component.

公开(公告)号：US11879413B2

公开(公告)日：2024-01-23

申请号：US17940480

申请日：2022-09-08

Applicant: ROLLS-ROYCE plc

Inventor： Paul R Davies ,  Gareth E Moore ,  Stephen M Husband ,  David R Trainer ,  David P Scothern ,  Luke George

IPC: F02K3/06 ,  F01D15/10 ,  F02C7/141

CPC classification number: F02K3/06 ,  F01D15/10 ,  F02C7/141 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2260/213 ,  F05D2260/606

Abstract: An aircraft gas turbine engine includes a heat exchanger module, and a core engine. The core engine includes an intermediate-pressure compressor, high-pressure compressor, and high and low-pressure turbines. The high-pressure compressor rotationally connects to the high-pressure turbine by a first shaft, and the intermediate-pressure compressor rotationally connects to the low-pressure turbine by a second shaft. The heat exchanger module fluidly communicates with the core engine by an inlet duct. The heat exchanger module includes a central hub and multiple heat transfer elements extending radially from the hub and spaced in a circumferential array, for heat energy transfer from a first fluid within the elements to an inlet airflow passing over a surface of the elements prior to airflow entry into an inlet to the core engine. The gas turbine engine further includes a first electric machine rotationally connected to the first shaft, and positioned downstream of the heat exchanger module.