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公开(公告)号：US20240361218A1
公开(公告)日：2024-10-31
申请号：US18647507
申请日：2024-04-26
Applicant: ROLLS-ROYCE plc
Inventor： Akhil MULLOTH
IPC: G01N1/42 , G01N23/046
CPC classification number: G01N1/42 , G01N23/046 , G01N2223/3103 , G01N2223/63
Abstract: A method for scanning at least one component includes placing the at least one component inside a storage vessel; filling the storage vessel with a cryogenic material; cooling the at least one component; placing the storage vessel between an x-ray source and a detector of a CT scanner; generating, via the x-ray source, an x-ray cone beam after cooling of the component that passes through the storage vessel while the at least one component is disposed within the storage vessel; receiving the x-ray cone beam at the detector; and generating an x-ray image of the at least one component.
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公开(公告)号：US12123362B2
公开(公告)日：2024-10-22
申请号：US18225427
申请日：2023-07-24
Applicant: ROLLS-ROYCE plc
Inventor： Peter Swann , Christopher P Madden , Craig W Bemment
CPC classification number: F02C9/40 , F02C9/28 , F23R3/343 , F05D2220/323 , F05D2270/08 , F05D2270/306 , F05D2270/31 , F05D2270/71
Abstract: An aircraft has first and second fuel sources containing fuels with different characteristics, and one or more gas turbine engines powered by the fuels and each having a staged combustion system having pilot and main fuel injectors and being operable in pilot-only and pilot-and-main ranges of operation. The gas turbine engines each have a fuel delivery regulator arranged to control fuel delivery to the pilot and main fuel injectors. The method includes: obtaining a proposed mission description; obtaining nvPM impact parameters for the gas turbine engines, the impact parameters being associated with each operating condition of the proposed mission; calculating an optimised set of one or more fuel characteristics for each flight condition of the proposed flight defined in the flight description based on the nvPM impact parameters; and determining a fuel allocation based on the optimised set of one or more fuel characteristics.
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公开(公告)号：US12123351B2
公开(公告)日：2024-10-22
申请号：US17484897
申请日：2021-09-24
Applicant: ROLLS-ROYCE plc
Inventor： Natalie C Wong , Thomas S Binnington , David A Jones , Daniel Blacker
CPC classification number: F02C7/18 , F01D25/12 , F02C7/04 , F02C7/143 , F02C7/185 , F02K3/065 , F05D2260/213 , F05D2260/232 , F05D2260/36 , F05D2260/606
Abstract: A turbofan gas turbine engine comprises, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, and a turbine module. The fan assembly comprises a plurality of fan blades defining a fan diameter (D), and the heat exchanger module comprises a plurality of heat exchanger elements. The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, with the heat exchanger module having an axial length along a central axis between an upstream-most face of the heat exchanger elements and a downstream-most face of the heat exchanger elements. The axial length is in the range of 0.1*D to 5.0*D.
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公开(公告)号：US12116933B2
公开(公告)日：2024-10-15
申请号：US18233521
申请日：2023-08-14
Applicant: ROLLS-ROYCE PLC
Inventor： Richard G Mochrie , David A Jones
CPC classification number: F02C7/14 , F02C7/16 , F02C7/224 , F05D2220/323 , F05D2260/213 , F05D2270/303
Abstract: A thermal management system for an aircraft comprises a first gas turbine engine, one or more first electric machines rotatably coupled to the first gas turbine engine, a first thermal bus, and a first heat exchanger module. The first thermal bus comprises a first heat transfer fluid, with the first heat transfer fluid being in fluid communication, in a closed loop flow sequence, between the first gas turbine engine, the or each first electric machine, and the first heat exchanger. Waste heat energy generated by at least one of the first gas turbine engine, and the or each first electric machine, is transferred to the first heat transfer fluid. The first heat exchanger module comprises a first flow path and a second flow path. The first flow path is configured to direct a flow of the first heat transfer fluid either to a first heat dissipation portion in which a first proportion QA of the waste heat energy from the first heat transfer fluid is transferred to a first dissipation medium, or additionally to a second heat dissipation portion in which a second proportion QB of the waste heat energy from the first heat transfer fluid is transferred to a second dissipation medium, in dependence on a temperature of the first heat transfer fluid entering the first heat exchanger module, a temperature of the first heat dissipation medium, and a temperature of the second heat dissipation medium. The second flow path is configured to direct the flow of the first heat transfer fluid to a second heat dissipation portion in which a second proportion QB of the waste heat energy from the first heat transfer fluid is transferred to a second dissipation medium, or additionally to the first heat dissipation portion in which a first proportion QA of the waste heat energy from the first heat transfer fluid is transferred to a first dissipation medium, in dependence on a temperature of the first heat transfer fluid entering the first heat exchanger module, a temperature of the first heat dissipation medium, and a temperature of the second heat dissipation medium.
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公开(公告)号：US20240339897A1
公开(公告)日：2024-10-10
申请号：US18602254
申请日：2024-03-12
Applicant: ROLLS-ROYCE plc
Inventor： Alexis LAMBOURNE , Christopher D. RILEY
IPC: H02K15/00 , H01F13/00 , H02K11/01 , H02K1/2783
CPC classification number: H02K15/0006 , H01F13/003 , H02K11/012 , H02K1/2783
Abstract: A method of magnetising or demagnetising an annular component for a rotary machine, a flux arrangement for performing a magnetising or demagnetising method, and a flux assembly for such a flux arrangement; wherein, the annular component includes an alternating arrangement of radial elements and angular elements for forming a Halbach array. A magnetizer is caused to induce magnetic flux in a primary set of elements of the annular component including a primary radial element and an adjacent primary angular element. A shield element shields a secondary angular element of the annular component from magnetic flux from the magnetizer.
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Patent Agency Ranking
公开(公告)号：US20240337218A1
公开(公告)日：2024-10-10
申请号：US18406296
申请日：2024-01-08
Applicant: ROLLS-ROYCE plc
Inventor： Benedict R. PHELPS
IPC: F02C7/36
CPC classification number: F02C7/36 , F05D2220/36
Abstract: A gas turbine engine for an aircraft comprises: an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan comprising a plurality of fan blades; a bypass duct delimited by a bypass duct inner wall and a bypass duct outer wall and located radially outwardly from the engine core and downstream of the fan; and an outlet guide vane assembly, located within the bypass duct and, comprising a plurality of outlet guide vanes distributed circumferentially within the bypass duct, each outlet guide vane extending radially along a span between the bypass duct inner wall and the bypass duct outer wall, wherein a space-chord ratio of at least one outlet guide vane, at 50% of the span length from the bypass duct inner wall, is less than 0.72.
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公开(公告)号：US12098684B2
公开(公告)日：2024-09-24
申请号：US18098433
申请日：2023-01-18
Applicant: ROLLS-ROYCE PLC
Inventor： Peter Swann , Christopher P Madden , Craig W Bemment
CPC classification number: F02C9/40 , F02C9/28 , F05D2220/323 , F05D2220/80 , F05D2270/306 , F05D2270/31
Abstract: A aircraft gas turbine engine and operation method, the engine including: a staged combustion system having pilot and main fuel injectors, and operates in a pilot-only range wherein fuel delivers to pilot fuel injectors, and a pilot-and-main operation range wherein fuel is delivered to at least the main fuel injectors. The engine further includes a fuel delivery regulator to pilot and main fuel injectors, which receives fuel from a first and second source containing fuels each with different characteristics. The staged combustion system switches between pilot-only and pilot-and-main range operation when in steady cruise mode, the mode defining a boundary between first and second engine cruise operation range. The fuel delivery regulator delivers fuel to pilot fuel injectors during at least part of the first engine cruise operation with different fuel characteristics from fuel delivered to one or both pilot and main fuel injectors the second engine cruise operation range.
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公开(公告)号：US12098651B2
公开(公告)日：2024-09-24
申请号：US17847699
申请日：2022-06-23
Applicant: ROLLS-ROYCE plc
Inventor： Shahrokh Shahpar
IPC: F01D5/14
CPC classification number: F01D5/145 , F05D2230/10 , F05D2240/305 , F05D2240/306
Abstract: A method for shaping an aerofoil by: (a) defining an aerofoil having a nominal shape, the nominal shape defined by; a leading edge, a trailing edge, a root and a tip, a span extending from the root to the tip, a pressure surface and a suction surface extending from the leading edge to the trailing edge; a nominal camber line extending from the leading edge to the trailing edge; (b) defining an edge region on one of the pressure and/or suction surface which extends distance of at least 0.1% but no more than 10% of the camber line length from one of the leading edge or the trailing edge of the aerofoil; and (c) adapting the shape of the pressure and/or suction surface within the edge region such that the edge region of the aerofoil achieves an asymmetric profile with respect to the nominal camber line.
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公开(公告)号：US20240313622A1
公开(公告)日：2024-09-19
申请号：US18589701
申请日：2024-02-28
Applicant: ROLLS-ROYCE PLC
Inventor： Seamus D. GARVEY , Karuna KALITA
CPC classification number: H02K11/30 , F02C6/20 , F02C7/268 , H02K1/146 , H02K7/1823
Abstract: An electric machine includes a stator having a phase arrangement, and a rotor. The phase arrangement includes first and second legs connected in parallel at first and second primary junctions. The legs each include first and second coils connected in series through a first intermediate junction. The intermediate junctions are connected by a branch such that the phase arrangement is a bridge circuit. The phase arrangement permits an alignment current to flow between the primary junctions via the branch, the alignment current being conducted through an alignment current path passing through one coil of each leg. The phase arrangement includes a negative impedance converter to add a negative electrical impedance to the alignment current path by introducing additional electrical energy into the respective alignment current path. The alignment current causes a translational force to be applied to the rotor for maintaining alignment of the rotor with respect to the stator.
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公开(公告)号：US12092024B1
公开(公告)日：2024-09-17
申请号：US18601182
申请日：2024-03-11
Applicant: ROLLS-ROYCE plc
Inventor： Nicholas Grech , Jacopo Tacconi
Abstract: A gas turbine engine includes a core engine having a compressor, a combustor and a turbine in sequential air flow series. The engine further includes a fuel offtake configured and arranged to divert a portion of hydrogen fuel from a main fuel conduit, a burner configured and arranged to burn the portion of hydrogen fuel diverted from the main fuel conduit and a heat exchanger configured and arranged to transfer heat from exhaust gasses produced by the burner to hydrogen fuel in the main fuel conduit. At least first and second compressor bleed offtakes are at different pressure stages of the compressor, each being configured to bleed a portion of air from the compressor. At least first and second compressor bleed offtake valves are configured to control flow through the first and second bleed offtakes respectively. The burner is configured to receive bleed air from the compressor bleed offtakes.
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