公开(公告)号：US20240102652A1

公开(公告)日：2024-03-28

申请号：US18215271

申请日：2023-06-28

Applicant: ROLLS-ROYCE plc

Inventor： Ewan F THOMPSON

IPC: F23R3/00 ,  B21D53/84 ,  F23R3/42

CPC classification number: F23R3/002 ,  B21D53/84 ,  F23R3/42

Abstract: A liner for use with a gas turbine engine includes a first liner portion including a first upstream surface and a first downstream surface. The liner further includes a second liner portion spaced apart from the first liner portion. The second liner portion includes a second upstream surface and a second downstream surface. The second upstream surface faces the first downstream surface. Each of the first liner portion and the second liner portion at least circumferentially and radially extends with respect to a central axis. Each of the first liner portion and the second liner portion includes a substrate made of a metallic material and a wear resistant coating disposed on at least a portion of the substrate. The wear resistant coating is made of a polymeric material. The wear resistant coating at least forms the first downstream surface and the second upstream surface.

公开(公告)号：US11927378B2

公开(公告)日：2024-03-12

申请号：US18057270

申请日：2022-11-21

Applicant: ROLLS-ROYCE plc

Inventor： Chloe J. Palmer ,  Ian M. Bunce

IPC: F25B9/06 ,  F25B9/00 ,  F25B49/02 ,  G01N25/12

CPC classification number: F25B49/02 ,  F25B9/008 ,  F25B9/06 ,  G01N25/12 ,  F25B2309/061 ,  F25B2600/2515

Abstract: A sensor assembly is shown for sensing a crossing of the critical point in a system utilising a working fluid in a transcritical cycle passing through the critical point. A first broadband acoustic sensor is located upstream of a component and a second broadband acoustic sensor is located downstream of the component, each of which are arranged to detect high-frequency and low-frequency sounds caused by the crossing of the critical point. A flow regulation device regulates flow of working fluid through the component in response to the output of one or both of the first broadband acoustic sensor and the second broadband acoustic sensor, thereby adjusting the location of the crossing of the critical point.

公开(公告)号：US20240077025A1

公开(公告)日：2024-03-07

申请号：US18233619

申请日：2023-08-14

Applicant: ROLLS-ROYCE PLC

Inventor： Paul R DAVIES ,  David A JONES ,  Alexander T JOYCE ,  Richard G MOCHRIE

IPC: F02C7/16 ,  F02C6/18

CPC classification number: F02C7/16 ,  F02C6/18 ,  F05D2220/323 ,  F05D2260/213

Abstract: A thermal management system for an aircraft comprises a first gas turbine engine, a first thermal bus, a first heat exchanger, and a chiller. 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 first gas turbine engine, the first heat exchanger, and the chiller. Waste heat energy generated by the first gas turbine engine, is transferred to the first heat transfer fluid. The chiller is configured to lower a temperature of the first heat transfer fluid prior to the first heat transfer fluid being circulated through the gas turbine engine. The first heat is exchanger is configured to transfer the waste heat energy from the first heat transfer fluid to a dissipation medium.

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.