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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
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.
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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
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.
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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.
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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.
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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
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.
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Patent Agency Ranking
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
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.
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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
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.
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公开(公告)号：US20230358405A1
公开(公告)日：2023-11-09
申请号：US18168912
申请日：2023-02-14
Applicant: ROLLS-ROYCE plc
Inventor： Jonathan KNAPTON , Nicholas M. BROWN
Abstract: A fuel spray nozzle includes a fuel circuit having in series a gallery, circumferentially spaced passages arranged in a row around the nozzle, and an annular spin chamber. Each passage has an inlet for receiving a respective portion of the fuel from the gallery and a metering orifice for discharging its portion of the fuel. The passages are configured such that, when the flow of liquid fuel to the inlet port is shut off, a respective differential static pressure develops across stagnant liquid fuel remaining between the inlet and the metering orifice of each passage, and the passages are further configured such that one or more selected passages develop a different differential static pressure to the remaining passages causing a flow of purging air to enter the gallery from the combustor through the selected passages and exit through the remaining passages, thereby purging the gallery and the passages of fuel.
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公开(公告)号：US11811283B2
公开(公告)日：2023-11-07
申请号：US17007338
申请日：2020-08-31
Applicant: ROLLS-ROYCE plc
Inventor： David F. Brookes
IPC: H02K3/28 , H02K1/16 , H02K3/14 , H02K3/24 , H02K3/42 , H02K3/493 , H02K15/00 , H02K15/02 , H02K15/085 , H02K15/12 , H02K21/14 , H02K7/18 , H02K9/197
CPC classification number: H02K3/28 , H02K1/165 , H02K3/14 , H02K3/24 , H02K3/42 , H02K3/493 , H02K7/1823 , H02K9/197 , H02K15/0018 , H02K15/024 , H02K15/085 , H02K15/12 , H02K21/14 , H02K2213/06
Abstract: A stator for a radial-flux rotary electric machine includes a yoke with a plurality of teeth, each tooth extending from a root at the yoke to a tip. The stator further includes a plurality of coils, each one of which being located on a respective one of the plurality of teeth, the coils being sized such that a slot fill factor is between zero and unity to define axial voids in the slots. The stator further includes a plurality of magnetic sealing members, each one of which being engaged with the tips of adjacent teeth to circumferentially and axially seal the axial voids in the slots for retaining an axial flow of coolant therein, the magnetic sealing members being composed of a magnetic material to provide a flux path between adjacent tooth tips to increase an amount of leakage flux.
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公开(公告)号：US20230349301A1
公开(公告)日：2023-11-02
申请号：US18219967
申请日：2023-07-10
Applicant: ROLLS-ROYCE plc
Inventor： Mark SPRUCE
CPC classification number: F01D25/18 , F02C7/36 , F16H57/0469 , F16H57/0479 , F02C7/06 , F02K3/06 , F02C3/113 , F01D25/166 , F16H2057/085
Abstract: Gearboxes for aircraft gas turbine engines, in particular to arrangements for journal bearings such gearboxes, and to related methods of operating such gearboxes and gas turbine engines. Example embodiments include a gearbox for an aircraft gas turbine engine, the gearbox including: a sun gear; a plurality of planet gears surrounding and engaged with the sun gear; and a ring gear surrounding and engaged with the plurality of planet gears, each of the plurality of planet gears being rotatably mounted around a pin of a planet gear carrier with a journal bearing having an internal sliding surface on the planet gear and an external sliding surface on the pin.
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