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公开(公告)号：US11480112B2
公开(公告)日：2022-10-25
申请号：US16892690
申请日：2020-06-04
Applicant: ROLLS-ROYCE plc
Inventor： Paul D Whatley
IPC: F02C9/48
Abstract: A gas turbine engine for an aircraft comprises a high-pressure (HP) spool comprising an HP compressor and a first electric machine driven by an HP turbine; a low-pressure (LP) spool comprising an LP compressor and a second electric machine driven by an LP turbine; a combustion system comprising a fuel metering unit; and an engine controller configured to, in response to a change of a throttle lever angle setting indicative of an acceleration event, increase fuel flow to the combustion system by the fuel metering unit, and to operate the first electric machine in a motor mode to increase the HP spool rotational speed and engine core mass flow.
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公开(公告)号：US20220328914A1
公开(公告)日：2022-10-13
申请号：US17226954
申请日：2021-04-09
Inventor： Michael Adam Zagrodnik , Stephen Mountain , Peter Schenk , Mathivanan Anand Prabhu , Krishnamoorthi Sivalingam , Teh Yee Siang , Chandana Jayampathi Gajanayake , Melvin Yang Yueng Yap
IPC: H01M50/143 , H01M50/383 , H01M10/04 , H01M50/179 , H01M50/119
Abstract: A battery housing for an aerospace battery may include a first endplate; a flange; and an elliptical cylinder extending from a first cylinder end to a second cylinder end. The first cylinder end of the elliptical cylinder may be welded to the first endplate, and the second cylinder end of the elliptical cylinder may be welded to the flange. The elliptical cylinder is formed from a sheet of material comprising a first sheet end and a second sheet end. The first sheet end may be welded to the second sheet end at a weld location that runs from the first cylinder end to the second cylinder end at a perimeter location that is calculated to experience a reduced stress during pressurization of the housing.
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公开(公告)号：US20220328913A1
公开(公告)日：2022-10-13
申请号：US17226863
申请日：2021-04-09
Inventor： Michael Adam Zagrodnik , Stephen Mountain , Peter Schenk , Mathivanan Anand Prabhu , Krishnamoorthi Sivalingam , Teh Yee Siang , Chandana Jayampathi Gajanayake , Melvin Yang Yueng Yap
IPC: H01M50/143 , H01M10/6556 , H01M50/249 , H01M10/6554 , H01M50/213 , H01M50/117
Abstract: An aerospace battery may include a housing; a battery pack core; a ceramic felt surrounding at least part of the battery pack core; and a closed cell foam filling open space between the battery pack core, the ceramic felt, and the housing.
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公开(公告)号：US11466856B2
公开(公告)日：2022-10-11
申请号：US17317073
申请日：2021-05-11
Applicant: ROLLS-ROYCE plc
Inventor： Michael Yeandel
Abstract: An afterburner arrangement comprising: an internal casing and an external casing defining a bypass pathway between them; a mounting strut forming a structural connection between the internal casing and the external casing; and A plurality of fuel nozzles associated with the mounting strut, wherein the mounting strut at least partly houses a corresponding plurality of fuel pathways to provide fuel to the respective fuel nozzles.
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公开(公告)号：US11459893B2
公开(公告)日：2022-10-04
申请号：US17212554
申请日：2021-03-25
Applicant: ROLLS-ROYCE PLC
Inventor： Nicholas Howarth , Gareth M Armstrong
IPC: F01D5/14 , F02C7/04 , F02C3/02 , F02C7/36 , F04D29/68 , F04D19/02 , F01D5/28 , F02C3/04 , F02C3/107 , F02K3/06 , F02K3/068
Abstract: A gas turbine engine that has improved fuel burn provides operability and/or maintenance requirements when installed on an aircraft. The gas turbine engine is provided with a core compressor that includes twelve, thirteen or fourteen rotor stages. The gas turbine engine has a ratio of a core compressor aspect ratio divided by a core compressor pressure ratio is in the range of from 0.03 to 0.09. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft.
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Patent Agency Ranking
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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