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公开(公告)号：US20220309846A1
公开(公告)日：2022-09-29
申请号：US17655689
申请日：2022-03-21
Applicant: Rolls-Royce plc
Inventor： Peter A. BEECROFT , Stefano LORETI , Dongfeng SHI
Abstract: A computer-implemented method for determining damage to an aircraft, the computer-implemented method comprising: (i) receiving first data from a first sensor, the first data comprising values for a first parameter of an aircraft; (ii) determining whether damage has occurred to the aircraft using the values of the first data; (iii) receiving second data from a second sensor, the second data comprising values for a second parameter of the aircraft; (iv) determining whether damage has occurred to the aircraft using the values of the second data; and (v) controlling output of a signal comprising data indicating the occurrence of damage to the aircraft using an occurrence of damage determined at step (ii) and/or an occurrence of damage determined at step (iv).
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公开(公告)号：US20220307448A1
公开(公告)日：2022-09-29
申请号：US17586401
申请日：2022-01-27
Applicant: ROLLS-ROYCE plc
Inventor： Roderick M. TOWNES , Pascal DUNNING , Michael J. WHITTLE
Abstract: A highly efficient gas turbine engine is provided. The fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.
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公开(公告)号：US20220298975A1
公开(公告)日：2022-09-22
申请号：US17827214
申请日：2022-05-27
Applicant: ROLLS-ROYCE plc
Inventor： Mark SPRUCE
Abstract: Gearboxes for aircraft gas turbine engines, in particular arrangements for journal bearings such gearboxes, and related methods of operating such gearboxes and gas turbine engines. A gearbox for an aircraft gas turbine engine includes: 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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公开(公告)号：US11440273B2
公开(公告)日：2022-09-13
申请号：US16367350
申请日：2019-03-28
Applicant: ROLLS-ROYCE plc
Inventor： Vincent Gill
Abstract: A method of forming a composite article involves the steps of: providing a formed article, the formed article comprising a plurality of non-crimp fibre fabrics with each non-crimp fibre fabric comprising at least two dry-fibre layers; stabilising the plurality of non-crimp fibre fabrics; machining a surface of the formed article having exposed ply terminations to provide a smooth blended surface with chamfered plydrops; positioning the machined formed article in a second mould; infiltrating the second mould with a polymer matrix resin; and curing the machined formed article to form the composite article.
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公开(公告)号：US20220281608A1
公开(公告)日：2022-09-08
申请号：US17545302
申请日：2021-12-08
Applicant: ROLLS-ROYCE PLC
Inventor： Graham P. BRUCE
Abstract: Electrical power systems for distributing electrical power in aircraft are described. One such electrical power system comprises: an electrical power source configured to output a number R≥2 of dc power channels, each dc power channel having a respective index r=(1, . . . , R); and a group of N dc load channels connected to the R dc power channels by a switching arrangement, wherein N>R and each dc load channel has a respective index n=(1, . . . , N). The system further comprises, for each respective one of a plurality of the N load channels, a current limiting device (CLD) operable to limit an amount of current flowing from the power channels to a load connectable to the electrical power system via the respective load channel. The electrical power source may comprise one or more batteries.
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Patent Agency Ranking
公开(公告)号：US11434832B2
公开(公告)日：2022-09-06
申请号：US17411617
申请日：2021-08-25
Applicant: ROLLS-ROYCE plc
Inventor： Craig W Bemment
Abstract: A gas turbine engine for an aircraft and a method of operating a gas turbine engine on an aircraft. Embodiments disclosed include a gas turbine engine for an aircraft including: an engine core has a turbine, a compressor, and a core shaft; a fan located upstream of the engine core, the fan has a plurality of fan blades; a nacelle surrounding the engine core and defining a bypass duct and bypass exhaust nozzle; and a gearbox that receives an input from the core shaft and outputs drive to the fan wherein the gas turbine engine is configured such that a jet velocity ratio of a first jet velocity exiting from the bypass exhaust nozzle to a second jet velocity exiting from an exhaust nozzle of the engine core at idle conditions is greater by a factor of 2 or more than the jet velocity ratio at maximum take-off conditions.
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公开(公告)号：US20220275763A1
公开(公告)日：2022-09-01
申请号：US17742620
申请日：2022-05-12
Applicant: ROLLS-ROYCE plc , ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
Inventor： Jorge CALDERON , David BROWN
Abstract: A gas turbine engine for an aircraft. The engine including: an engine core with a turbine, a compressor, a fan located upstream of the compressor and including a plurality of fan blades, and a core shaft connecting the turbine to the compressor; a gearbox which receives an input from the core shaft and outputs drive, via a driveshaft, to the fan so as to drive the fan at a lower rotational speed than the turbine, the drive shaft and core shaft forming a shaft system.
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公开(公告)号：US11428169B2
公开(公告)日：2022-08-30
申请号：US17096175
申请日：2020-11-12
Applicant: ROLLS-ROYCE plc , Rolls-Royce Corporation
Inventor： Simon J. Donovan , Peter E. Daum , Siddharth Ravichandran
Abstract: An abradable sealing element comprises a substrate and a sealing structure. The sealing structure comprises one or more wall structures extending from the substrate and defining at least one open cell which is filled with abradable material. The one or more wall structures are formed by additive-layer, powder-fed, laser-weld deposition onto the substrate. The one or more wall structures are formed from nickel-based superalloy and constitute from about 10% to about 50% of the total volume of the sealing structure.
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公开(公告)号：US20220268216A1
公开(公告)日：2022-08-25
申请号：US17731673
申请日：2022-04-28
Applicant: ROLLS-ROYCE plc
Inventor： Roderick M TOWNES , Michael J WHITTLE , Pascal DUNNING
Abstract: A highly efficient gas turbine engine is a system wherein the fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.
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公开(公告)号：US11421552B2
公开(公告)日：2022-08-23
申请号：US17205870
申请日：2021-03-18
Applicant: ROLLS-ROYCE plc
Inventor： Mark Spruce
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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