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公开(公告)号：US12240983B2
公开(公告)日：2025-03-04
申请号：US18062041
申请日：2022-12-06
Applicant: ROLLS-ROYCE plc
Inventor： John R. Nicholls , Victoria Louise Minns , David S. Rickerby
Abstract: A method of forming a protective coating. The method includes providing a substrate including at least one chemical element and a surface; forming a basecoat composition including an aluminium phase including aluminium; applying the basecoat composition on the surface of the substrate to form a basecoat layer; heating the basecoat layer to a first temperature for a predetermined period of time; applying a glow discharge plasma on the basecoat layer; and heating the basecoat layer to a second temperature greater than the first temperature, in order to activate an exothermic reaction between at least the aluminium phase of the basecoat layer and the at least one chemical element of the substrate, wherein the exothermic reaction forms the protective coating on the surface of the substrate.
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公开(公告)号：US12240614B2
公开(公告)日：2025-03-04
申请号：US18209136
申请日：2023-06-13
Applicant: ROLLS-ROYCE plc
Inventor： Peter Swann , Craig W Bemment , Alastair G Hobday , Benjamin J Keeler , Christopher P Madden
Abstract: A power system for an aircraft includes one or more gas turbine engines arranged to burn a fuel so as to provide power to the aircraft; a plurality of fuel tanks each arranged to contain a fuel to be used to provide power to the aircraft; and a fuel manager. At least two of the fuel tanks contain different fuels, which have different proportions of a sustainable aviation fuel. The fuel manager is arranged to store information on the fuel contained in each fuel tank; and to control fuel supply so as to select a specific fuel accordingly to power at least the majority of operations on the ground. The fuel manager may additionally identify which tank contains the fuel with the highest proportion of a sustainable aviation fuel; and that fuel may be used to power at least the majority of operations on the ground.
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公开(公告)号：US20250067434A1
公开(公告)日：2025-02-27
申请号：US18804670
申请日：2024-08-14
Applicant: ROLLS-ROYCE PLC
Inventor： Marcin Damian DUTKA
Abstract: A tile for a gas turbine engine combustor. The tile has a base that has a hot-side surface, a cold-side surface, a first circumferential extremity, a second circumferential extremity and a local radial axis. The tile also has a plurality of cooling channels that have inlets on the cold-side surface and outlets on the hot-side surface, and one or more rail structure attached to the cold-side surface of the base.
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公开(公告)号：US12234019B2
公开(公告)日：2025-02-25
申请号：US18045857
申请日：2022-10-12
Applicant: ROLLS-ROYCE plc
Inventor： Christopher A Murray
Abstract: A cabin blower system, for an aircraft, comprising: a cabin blower compressor, for compressing air for delivery to a cabin of an aircraft, comprising a compressor drive shaft running on a contactless bearing system; and a transmission comprising an input and an output, the input being arranged to receive power from an engine of the aircraft and the output being arranged to mechanically drive the cabin blower compressor, wherein the output of the transmission is mechanically coupled with the compressor drive shaft via a flexible drive coupling.
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公开(公告)号：US12228077B2
公开(公告)日：2025-02-18
申请号：US18183989
申请日：2023-03-15
Applicant: ROLLS-ROYCE plc
Inventor： Jonathan E. Holt , Richard Sharpe
Abstract: Disclosed is a fuel system for a gas turbine engine. The system comprises a fuel pump for fluid communication with a fuel reservoir; a driving turbine for driving the fuel pump; and a source of compressed air flow to drive the driving turbine. The source of compressed air may be the engine core, a dedicated fuel system compressor or the compressor of a cabin blower system.
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Patent Agency Ranking
公开(公告)号：US20250052425A1
公开(公告)日：2025-02-13
申请号：US18772375
申请日：2024-07-15
Applicant: ROLLS-ROYCE plc
Inventor： Stephen C. HARDING , Paul A. HUCKER , Iain MORGAN
IPC: F23R3/00
Abstract: The present disclosure relates to a combustor assembly for a gas turbine engine. The combustor assembly comprises a combustor liner, a combustor head, a cowl and a fastener. The combustor liner and the cowl define a cavity. The combustor liner has an integral lug that extends into the cavity from a wall of the combustor liner. The fastener extends into the combustor liner lug to fasten the combustor head to the combustor liner.
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公开(公告)号：US12224673B2
公开(公告)日：2025-02-11
申请号：US17956968
申请日：2022-09-30
Applicant: ROLLS-ROYCE plc
Inventor： David R. Trainer , Francisco Javier Chivite Zabalza , Mark Sweet , Luke George
Abstract: There is provided an electrical power system comprising: a DC voltage source, a DC electrical network, a DC to AC to DC converter having a primary side connected to the DC voltage source and a secondary side connected to the DC electrical network, and a controller configured to control the DC to AC to DC converter, wherein the controller is configured to: monitor an electrical current or voltage between the DC voltage source and the DC electrical network; determine, based on the monitored electrical current or voltage, whether the DC electrical network is in a fault condition; and increase a switching frequency of the primary side of the DC to AC to DC converter in response to a positive determination that the DC electrical network is in a fault condition.
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公开(公告)号：US20250035050A1
公开(公告)日：2025-01-30
申请号：US18433932
申请日：2024-02-06
Applicant: Rolls-Royce plc
Inventor： Mark SPRUCE
Abstract: Gas turbine engine for aircraft includes: an engine core including a turbine, compressor, and core shaft connecting the turbine to the compressor; a fan located upstream of the core; a gearbox; and a gearbox support arranged to at least partially support the gearbox. The fan has a mass in a range of 150 kg to 1200 kg. A moment of inertia of the fan is greater than or equal to 7.40×107 kgmm2. A radial bending stiffness to moment of inertia ratio of: the radial bending stiffness of at least one of the fan shaft at the output of the gearbox and the gearbox support the moment of inertia of the fan may be greater than or equal to 2.5×10−2 Nkg−1 m−1 mm−2. A tilt stiffness to moment of inertia ratio of: the tilt stiffness of at least one of the fan shaft at the output of the gearbox and the gearbox support the moment of inertia of the fan may be greater than or equal to 4.0×10−4 Nmrad−1 kg−1 mm−2.
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公开(公告)号：US20250035037A1
公开(公告)日：2025-01-30
申请号：US18913201
申请日：2024-10-11
Applicant: ROLLS-ROYCE PLC
Inventor： Richard G. Stretton , Michael C. Willmot , Nicholas Grech
Abstract: A gas turbine engine (10) for an aircraft comprises an engine core (11) comprising a turbine (19), a compressor (14), a core shaft (26), and a core exhaust nozzle (20), the core exhaust nozzle (20) having a core exhaust nozzle pressure ratio calculated using total pressure at the core nozzle exit (56); a fan (23) comprising a plurality of fan blades; and a nacelle (21) surrounding the fan (23) and the engine core (11) and defining a bypass duct (22), the bypass duct (22) comprising a bypass exhaust nozzle (18), the bypass exhaust nozzle (18) having a bypass exhaust nozzle pressure ratio calculated using total pressure at the bypass nozzle exit;
wherein a bypass to core ratio of: bypass exhaust nozzle pressure ratio core exhaust nozzle pressure ratio is configured to be in the range from 1.1 to 2.0 under aircraft cruise conditions.-
公开(公告)号：US12203379B2
公开(公告)日：2025-01-21
申请号：US18594226
申请日：2024-03-04
Applicant: ROLLS-ROYCE PLC
Inventor： Guy Stevenson
Abstract: A temperature measurement system for a gas turbine engine, the gas turbine engine including, in axial flow sequence, a compressor section, a combustor section having plural fuel spray nozzles, and a turbine section. The temperature measurement system includes one or more optical thermometers, each optical thermometer configured to measure the temperature of a component washed by the working gas of the engine, the or each component being in the combustor section or the turbine section at a first position along the axis of the engine.
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