公开(公告)号：US20230398632A1

公开(公告)日：2023-12-14

申请号：US18322916

申请日：2023-05-24

Applicant: ROLLS-ROYCE plc

Inventor： Adam CLARE ,  Andres A. GAMEROS MADRIGAL ,  James KELL ,  Andrew D. NORTON ,  Thomas GIRERD

IPC: B23K26/26 ,  B23P6/00

CPC classification number: B23K26/26 ,  B23P6/00

Abstract: A repair system for in-situ repair of a machine. The repair system includes a laser unit configured to emit a laser beam, a galvanometer optically coupled to the laser unit and configured to adjust the laser beam received from the laser unit, a source of a flexible metallic mesh, a delivery unit configured to receive the flexible metallic mesh from the source of the flexible metallic mesh, and a controller communicably coupled to the laser unit, the galvanometer, and the delivery unit. The controller is configured to control the delivery unit to deposit the flexible metallic mesh on a surface of the machine. The controller is further configured to control the laser unit to emit the laser beam and to control the galvanometer to adjust the laser beam in order to weld the flexible metallic mesh to the surface of the machine, thereby forming a repair patch.

公开(公告)号：US11840965B2

公开(公告)日：2023-12-12

申请号：US17980230

申请日：2022-11-03

Applicant: ROLLS-ROYCE plc

Inventor： Mark Spruce

IPC: F02C7/36 ,  F16H1/28 ,  F16H57/02

CPC classification number: F02C7/36 ,  F16H1/28 ,  F16H2057/02039

Abstract: A gas turbine engine for an aircraft configured with an engine core that has a turbine, a compressor, and a core shaft connecting the turbine to the compressor. A fan located upstream of the engine core, that has a plurality of fan blades. A gearbox arranged to receive an input from the core shaft and to output to the fan so as to drive the fan at a lower rotational speed than the core shaft. The gearbox being an epicyclic gearbox having a sun gear, a plurality of planet gears, a ring gear, and a planet carrier on which the planet gears are mounted. The gearbox having an overall gear mesh stiffness, and wherein the overall gear mesh stiffness of the gearbox is greater than or equal to 1.05×109 N/m and less than or equal to 8.0×109 N/m.

公开(公告)号：US11837894B2

公开(公告)日：2023-12-05

申请号：US17957778

申请日：2022-09-30

Applicant: Rolls-Royce plc

Inventor： David R Trainer ,  Francisco Javier Chivite Zabalza ,  Mark Sweet ,  Gian Incerpi ,  Luke George

IPC: H02J7/00 ,  H02M3/335 ,  B64D27/24

CPC classification number: H02J7/0031 ,  B64D27/24 ,  H02M3/33573 ,  B64D2221/00 ,  H02J2207/20

Abstract: An electrical power system including: an electrical power source, a power electronics converter, an electrical network, a current limiting diode and a controllable circuit interruption device, wherein: the current limiting diode is configured to limit a fault current passing between the electrical power source and the electrical network in a fault condition; and the controllable circuit interruption device is configured to interrupt the fault current in response to a determination that the electrical power system is in the fault condition.

公开(公告)号：US20230383697A1

公开(公告)日：2023-11-30

申请号：US18302096

申请日：2023-04-18

Applicant: ROLLS-ROYCE plc

Inventor： Matthew S. CARTWRIGHT ,  Michael YEANDEL

IPC: F02C7/36 ,  B64D35/00 ,  B64D27/10 ,  B64D27/24 ,  F02C3/04

CPC classification number: F02C7/36 ,  B64D35/00 ,  B64D27/10 ,  B64D27/24 ,  F02C3/04

Abstract: Disclosed is an aircraft accessory drive system comprising: a drive shaft configured to provide a drive input; a critical accessory directly coupled to the drive shaft so as to be directly driven by the drive shaft; a parasitic drive system configured to transmit drive input from the drive shaft to one or more less critical accessories, wherein the parasitic drive system comprises a torque limiter configured to decouple the parasitic drive system from the drive shaft and the critical accessory in response to a jam affecting the parasitic drive system or one or more of the less critical accessories. Also disclosed are a gas turbine engine comprising an aircraft accessory drive system, and an aircraft comprising an aircraft accessory drive system.

公开(公告)号：US20230383694A1

公开(公告)日：2023-11-30

申请号：US18310747

申请日：2023-05-02

Applicant: ROLLS-ROYCE plc

Inventor： Chloe Jo PALMER

IPC: F02C3/22 ,  F02C7/224 ,  F02C3/06 ,  B64D15/04 ,  B64D37/30 ,  B64D37/34 ,  B64D13/08

CPC classification number: F02C3/22 ,  F02C7/224 ,  F02C3/06 ,  B64D15/04 ,  B64D37/30 ,  B64D37/34 ,  B64D13/08

Abstract: A hydrogen-fuelled gas turbine engine has a fuel input path from a fuel input of the engine to a combustor, the engine further comprising a heat-exchanger located in the fuel input path and a fuel turbine located in the fuel input path between the heat-exchanger and the combustor. The heat-exchanger is arranged to receive waste heat from the engine core in order to heat hydrogen fuel introduced at the fuel input prior to input thereof to the combustor. The engine further comprises an air compressor arranged to be driven by the fuel turbine. The engine provides for most of the waste heat of combustion to be recovered and used without the need for heavy electrical or mechanical apparatus and is therefore particularly advantageous in aeronautical applications.

公开(公告)号：US11828198B2

公开(公告)日：2023-11-28

申请号：US17748379

申请日：2022-05-19

Applicant: ROLLS-ROYCE plc

Inventor： Crispin Bolgar ,  Steven Radomski

IPC: F01D9/04

CPC classification number: F01D9/042 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/12

Abstract: A vane for a gas turbine engine, the vane including a platform with an airfoil extending radially from the upper surface of the platform. The platform includes a joint portion which includes a circumferentially extending flange and a recessed surface both formed on either the upper or lower surface of the platform. The flange and the recessed surface extend from opposing circumferential edges of the joint portion and each include a substantially radially-extending through hole.

公开(公告)号：US20230374667A1

公开(公告)日：2023-11-23

申请号：US18138213

申请日：2023-04-24

Applicant: ROLLS-ROYCE PLC

Inventor： Glen PATTINSON ,  Matthew C APPLETON

IPC: C23C24/04

CPC classification number: C23C24/04

Abstract: A method for improving the corrosion and fatigue crack resistance of an article that has a surface. The method involves: providing a dry powder having one or more anti-corrosion materials; pressurising the dry powder to 1 to 5 MPa in an inert gas; pre-heating the surface of the article to a temperature of 50 to 900° C. and cold-spraying the surface of the article with the dry powder at a particle velocity of 300 to 1200 m/s so that a corrosion and crack-resistant coating is formed on the surface of the article and the surface is modified to an average depth of 10 to 100 μm.

公开(公告)号：US20230373635A1

公开(公告)日：2023-11-23

申请号：US18163143

申请日：2023-02-01

Applicant: ROLLS-ROYCE plc

Inventor： Christopher A. MURRAY

IPC: B64D13/02 ,  F02C6/08

CPC classification number: B64D13/02 ,  F02C6/08 ,  F05D2220/323

Abstract: There is provided an air pressurisation system comprising: a blower compressor coupled to a spool of a gas turbine engine and configured to receive inlet air from a bypass duct of the gas turbine engine; an air treatment apparatus to mix air from the air cycle line with air from the bypass line to control a temperature of air for discharge to an airframe system; and a core bleed line configured to provide a second inlet flow of air from a compressor of the gas turbine engine to the air treatment apparatus in an augmented air supply mode of the air pressurisation system; wherein the core bleed line is configured to provide the second inlet flow of air directly to the bypass line or mix the second inlet flow of air with air from the blower compressor upstream of the bypass line.

公开(公告)号：US11821373B2

公开(公告)日：2023-11-21

申请号：US18053124

申请日：2022-11-07

Applicant: ROLLS-ROYCE plc

Inventor： Christopher P. Madden ,  Peter Swann

IPC: F02C9/28 ,  F23R3/34 ,  F02C3/30 ,  F02C9/26 ,  F02C9/40

CPC classification number: F02C9/28 ,  F02C3/30 ,  F23R3/346 ,  F02C9/263 ,  F02C9/40 ,  F05D2270/08 ,  F05D2270/804

Abstract: A gas turbine engine for an aircraft. The gas turbine comprises a staged combustion system having pilot injectors and main injectors, a fuel metering system configured to control fuel flow to the pilot injectors and the main injectors, and a fuel system controller. The controller is configured to identify an atmospheric condition, determine a ratio of pilot fuel flow rate for the pilot injectors to main fuel flow rate for the main injectors in response to the atmospheric condition, and inject fuel by the pilot injectors and the main injectors in accordance with said ratio to control an index of soot emissions caused by combustion of fuel therein.

公开(公告)号：US11815048B2

公开(公告)日：2023-11-14

申请号：US17398817

申请日：2021-08-10

Applicant: ROLLS-ROYCE plc

Inventor： Vasileios Kyritsis ,  Maurice Bristow ,  Peter Loftus

IPC: F02K3/075 ,  G01F1/66

CPC classification number: F02K3/075 ,  G01F1/66 ,  F05D2220/36 ,  F05D2260/40311 ,  F05D2260/606 ,  F05D2270/112 ,  F05D2270/303 ,  F05D2270/306 ,  F05D2270/80

Abstract: A turbofan gas turbine engine having a bypass duct, and a bypass airflow measurement system. The bypass airflow measurement system comprises: at least one acoustic transmitter configured to transmit an acoustic waveform across the bypass duct of the gas turbine engine though which a bypass airflow passes to at least one acoustic receiver; where the at least one acoustic transmitter and the at least one acoustic receiver are located on an axial plane that is substantially perpendicular to the bypass flow. A method of measuring bypass airflow properties of a turbofan gas turbine engine is also described.