公开(公告)号：EP4497926A1

公开(公告)日：2025-01-29

申请号：EP23204600.3

申请日：2023-10-19

Applicant: Rolls-Royce Corporation ,  Rolls-Royce North American Technologies Inc.

Inventor： LAWRENCE, Jeffrey ,  SCHENK, Peter ,  SCHETZEL II, Douglas Keith ,  HARRAL, Jacob Ward ,  HUBER, Brian Joseph

IPC: F02C7/277

Abstract: A starting apparatus for a first gas turbine engine of a plurality of gas turbine engines of an aircraft. The apparatus includes an air turbine starter, an electric machine, and a controller. The controller is configured to receive an emergency restart command for the first gas turbine engine while the aircraft is in-flight, determine whether the first gas turbine engine is in operation, determine whether at least a second gas turbine engine of the plurality of gas turbine engines is in operation, and, responsive to receiving the emergency restart command and determining that at least the second gas turbine engine of the plurality of gas turbine engines is in operation and that the first gas turbine engine is not in operation, perform an emergency restart of the first gas turbine engine.

公开(公告)号：EP4417798A1

公开(公告)日：2024-08-21

申请号：EP23204292.9

申请日：2023-10-18

Applicant: Rolls-Royce Corporation ,  Rolls-Royce North American Technologies Inc.

Inventor： HILL, Mathew ,  KABBES, Michael Joseph ,  MUNEVAR, Erik A. ,  SCHENK, Peter ,  HARRAL, Jacob Ward

IPC: F02C7/275 ,  F02C7/32 ,  F02C7/36 ,  F16D11/14 ,  F16D43/00

CPC classification number: F02C7/275 ,  F02C7/36 ,  F02C7/32 ,  F16D2011/00820130101 ,  F16D11/14 ,  F16D43/00 ,  F16D7/044

Abstract: In examples, a clutch assembly includes a first clutch member disposed near a first end of a first shaft. The first clutch member defines a first surface. The first shaft includes a starter motor coupled to a second end of the first shaft. The clutch assembly includes a second clutch member disposed near a first end of a second shaft. The second clutch member defines a second surface opposing the first surface, and the second shaft includes an accessory gearbox of a gas turbine engine coupled to a second end of the second shaft. The surfaces of the first and second clutch member engage such that rotational motion is transferred between the first clutch member and the second clutch member. The first clutch member and the second clutch member are configured to passively disengage from each other and actively reengage with each other.

公开(公告)号：EP4345257A1

公开(公告)日：2024-04-03

申请号：EP23186415.8

申请日：2023-07-19

Applicant: Rolls-Royce plc ,  Rolls-Royce Corporation

Inventor： SHANMUKHA, Rama Krishna ,  MATHIVANAN, Anand P. ,  LOH, Jenn Yen

IPC: F01D15/10 ,  F01D25/12 ,  H02K5/18 ,  H02K9/06

Abstract: An electric machine (20) for use in an aircraft propulsion system includes a shaft (28), a magnetic rotor drum (30), and a rotor hub (32). The shaft extends along an axis (11) and is configured to rotate about the axis. The magnetic rotor drum includes a rotor drum body (34) that extends circumferentially around the axis and a plurality of magnets (36) that are arranged circumferentially around the rotor. The rotor hub includes an end cap (42A) and an impeller (44A) that extend radially between and interconnect the shaft and the rotor drum body. The rotor hub is configured to move air axially along the shaft toward the rotor drum body to cool components thereof in response to rotation of the shaft about the axis.

公开(公告)号：EP4215731A1

公开(公告)日：2023-07-26

申请号：EP22214878.5

申请日：2022-12-20

Applicant: Rolls-Royce plc ,  Rolls-Royce Corporation

Inventor： Murray, Christopher A ,  Howarth, Nicholas ,  Swain, Daniel ,  Bousfield, Ian J

IPC: F02C6/08 ,  F02C7/277 ,  F02C7/32

Abstract: There is provided a blower system 400 for providing air to an airframe system 450, comprising a rotor 410 configured to be mechanically coupled to a spool 440 of a gas turbine engine 10, wherein the rotor 410 is configured to: in a blower mode, be driven to rotate by the spool 440 to discharge air to an airframe discharge port 426 for supply to an airframe system 450; and, in an engine drive mode, receive air from an external air source 470 via an impingement port 424 that is configured to direct the received air onto the rotor and thereby drive the rotor to rotate to drive the spool 440 to.

公开(公告)号：EP4155012A1

公开(公告)日：2023-03-29

申请号：EP22196861.3

申请日：2022-09-21

Applicant: Rolls-Royce Corporation ,  The Penn State Research Foundation

Inventor： NELSON, Scott ,  THOMAS, Baily ,  NASSAR, Abdalla R. ,  SCHERER, Jason ,  GRUBBS, John

IPC: B22F10/25 ,  B22F12/90 ,  B23K26/14 ,  B23K26/144 ,  B23K26/342 ,  B23K35/02 ,  B33Y30/00 ,  B33Y40/00 ,  G01N15/02 ,  G06T7/00

Abstract: A powder flow monitoring system may include a computing device configured to receive image data representing illuminated powder of a powder stream between a powder delivery device and a build surface of a component, generate a representation of the powder stream based on the image data, and output the representation of the powder stream for display at a display device.

公开(公告)号：EP4095352A1

公开(公告)日：2022-11-30

申请号：EP22157437.9

申请日：2022-02-18

Applicant: Rolls-Royce Corporation

Inventor： FREEMAN, Ted J. ,  SIPPEL, Aaron D. ,  THOMAS, David J.

IPC: F01D9/04

Abstract: A turbine shroud assembly (20)adapted for use with a gas turbine engine includes a shroud segment (22) and a carrier (26). The shroud segment extends circumferentially partway around an axis to define a gas path boundary of the turbine shroud assembly. The carrier is configured to support the shroud segment in position radially relative to the axis.

公开(公告)号：EP3901425A1

公开(公告)日：2021-10-27

申请号：EP21164445.5

申请日：2021-03-24

Applicant: Rolls-Royce Corporation ,  Rolls-Royce plc ,  Rolls-Royce North American Technologies, Inc.

Inventor： Sadler, Keith ,  Freeman, Ted ,  Sippel, Aaron ,  Baucco, Alexandra

IPC: F01D25/24 ,  F01D11/18

Abstract: An assembly adapted for use in a gas turbine engine includes a carrier and a blade track segment. The carrier extends at least partway about an axis. The blade track segment is supported by the carrier radially relative to the axis to define a portion of a gas path of the assembly.

公开(公告)号：EP3879132A1

公开(公告)日：2021-09-15

申请号：EP21250001.1

申请日：2021-03-04

Applicant: Rolls-Royce Corporation

Inventor： Kleman, Donald

IPC: F16D23/04 ,  F16D27/06

Abstract: An electromagnetic clutch assembly (106) includes a first clutch plate (120), a second clutch plate (122), and a synchronizer (124). The second clutch plate defines an aperture (138). A portion of the synchronizer is configured to extend through the aperture. In the absence of a magnetic field, the first clutch plate and the first surface of the second clutch plate define an air gap (150) and the portion of the synchronizer extends into the air gap. In response to a first magnetic field, the portion of the synchronizer contacts the first clutch plate. In response to a second magnetic field, the portion of the synchronizer translates in the aperture toward the second clutch plate and the first clutch plate and the second clutch plate close the air gap.

公开(公告)号：EP3838486A1

公开(公告)日：2021-06-23

申请号：EP20207962.0

申请日：2020-11-17

Applicant: Rolls-Royce Corporation

Inventor： Shuck, Quinlan

IPC: B24D18/00 ,  B24D3/06 ,  B22F10/364 ,  B22F10/25 ,  B33Y10/00 ,  B33Y30/00 ,  F01D11/12 ,  B22F1/02

Abstract: A method for processing an abrasive coating after deposition of the abrasive coating to improve properties of the abrasive coating. The method involves: controlling, by a computing device, an energy delivery device to deliver energy to an abrasive coating, wherein the abrasive coating comprises a metal matrix and abrasive particles at least partially encapsulated by the metal matrix; and controlling, by the computing device, the energy delivery device to scan the energy across a surface of the abrasive coating and form a series of softened or melted portions of the metal matrix.

公开(公告)号：EP3825522A1

公开(公告)日：2021-05-26

申请号：EP20206441.6

申请日：2020-11-09

Applicant: Rolls-Royce plc ,  Rolls-Royce Corporation

Inventor： Donovan, Simon ,  Daum, Peter ,  Ravichandran, Siddharth

IPC: F01D11/12 ,  B22F5/00 ,  B33Y10/00 ,  B33Y80/00

Abstract: An abradable sealing element (100) comprises a substrate (104) and a sealing structure. The sealing structure comprises one or more wall structures (102) extending from the substrate (104) and defining at least one open cell (106) which is filled with abradable material (108). The one or more wall structures (102) are formed by additive-layer, powder-fed, laser-weld deposition onto the substrate (104). The one or more wall structures (102) are formed from nickel-based superalloy and constitute from about 10 % to about 50 % of the total volume of the sealing structure. A method of manufacturing such an abradable sealing element (100) is also disclosed.