Patents Assigned to Rolls-Royce plc
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Patent number: 11542890Abstract: A gas turbine engine generates noise during use, and one particularly important flight condition for noise generation is take-off. A gas turbine engine that has high efficiency provides low noise, in particular from the fan and the turbine that drives the fan. Values are defined for a noise parameter NP that results in a gas turbine engine having reduced combined fan and turbine noise.Type: GrantFiled: March 5, 2021Date of Patent: January 3, 2023Assignee: ROLLS-ROYCE PLCInventors: Alastair D Moore, Robert J Telling
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Patent number: 11542873Abstract: 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.Type: GrantFiled: May 27, 2022Date of Patent: January 3, 2023Assignee: ROLLS-ROYCE PLCInventor: Mark Spruce
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Publication number: 20220411954Abstract: A method of electropolishing an internal passageway of a component, wherein the passageway has an inlet and an outlet; including: providing an electrode assembly including a flexible electrode, a shuttle and a guide cable extending between the flexible electrode and the shuttle; inserting the shuttle into the inlet; causing fluid to flow through the passageway to transport the shuttle through the passageway from the inlet towards the outlet; pulling the guide cable through the passageway to position the electrode in the passageway adjacent to a region of the passageway to be polished; and electropolishing the passageway using the electrode while moving the electrode within the passageway. Also, an electrode assembly for electropolishing an internal passageway of a component, including: a flexible electrode, a shuttle, and a guide cable extending between the flexible electrode and the shuttle.Type: ApplicationFiled: June 16, 2022Publication date: December 29, 2022Applicant: ROLLS-ROYCE plcInventor: Daniel CLARK
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Publication number: 20220412269Abstract: A gas turbine engine has a compression system blade ratio defined as the ratio of the height of a fan blade to the height of the most downstream compressor blade in the range of from 45 to 95. 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.Type: ApplicationFiled: April 28, 2022Publication date: December 29, 2022Applicant: ROLLS-ROYCE PLCInventors: Nicholas HOWARTH, Gareth M. ARMSTRONG
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Publication number: 20220411583Abstract: A curable resin composition including a first bismaleimide compound, a second bismaleimide compound which is different from the first bismaleimide compound, and a cyanate ester monomer. A liquid processible bismaleimide-triazine resin is provided by curing the resin composition. A method of preparing the liquid processible bismaleimide-triazine resin is also disclosed.Type: ApplicationFiled: June 23, 2021Publication date: December 29, 2022Applicant: ROLLS-ROYCE plcInventors: Robert James EREDALE, Ian HAMERTON
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Publication number: 20220407144Abstract: Battery packs for aircraft are provided, as are aircraft comprising such battery packs. One such battery pack comprises: a housing enclosing a plurality of battery cells; and an air channel. The air channel is connectable to an aircraft air inlet and an aircraft air outlet whereby, during flight of the aircraft, air enters the aircraft through the air inlet, passes through the battery pack air channel and exits the aircraft through the air outlet. At least a portion of a surface of the air channel is in thermal contact with the battery cells, whereby air flowing through the air channel exchanges heat with the battery cells through the surface of the air channel without entering the housing and contacting the battery cells.Type: ApplicationFiled: May 23, 2022Publication date: December 22, 2022Applicant: ROLLS-ROYCE PLCInventors: Michael Adam ZAGRODNIK, Krishnamoorthi SIVALINGAM, Satyanarayana Reddy GAJJELA, Vidor VERES-SZÉKELY, Dániel LÖRINCZ, István ÖRÖKÖS-TÓTH, Anand Prabhu MATHIVANAN
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Publication number: 20220407135Abstract: Methods for thermally regulating batteries of aircraft are provided. The aircraft comprises: an air inlet; an air outlet; a battery pack comprising battery cells; and an air channel in fluid communication with the air inlet and the air outlet, a surface of the air channel being in thermal communication with the battery cells whereby air flowing through the air channel exchanges heat with the battery cells through the surface of the air channel. The methods comprise: connecting an external supply of air to the air inlet of the aircraft; and delivering a flow of air through the air channel using the external supply of air. A kit comprising the aircraft and the external supply of air is also provided.Type: ApplicationFiled: May 23, 2022Publication date: December 22, 2022Applicant: ROLLS-ROYCE plcInventors: Michael Adam ZAGRODNIK, Krishnamoorthi SIVALINGAM, Satyanarayana Reddy GAJJELA, Vidor VERES-SZEKELY, Daniel LORINCZ, István ÖRÖKÖS-TÓTH, Anand Prabhu MATHIVANAN, Umesh MAHAJAN, Rakesh MURALI
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Publication number: 20220403743Abstract: 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.Type: ApplicationFiled: August 22, 2022Publication date: December 22, 2022Applicant: ROLLS-ROYCE plcInventors: Nicholas HOWARTH, Gareth M ARMSTRONG
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Publication number: 20220402620Abstract: An aircraft including a battery pack having a plurality of battery cells arranged to vent into a venting region of the battery pack. A path is defined between the venting region and an exterior of the aircraft, whereby thermal products vented by the cells can exit the aircraft via the path. In some embodiments, the venting region is or is in fluid communication with an air channel through which air flows from an aircraft air inlet to an aircraft air outlet. In other embodiments, the path joins the venting region and an opening in an external surface of the aircraft.Type: ApplicationFiled: May 23, 2022Publication date: December 22, 2022Applicant: ROLLS-ROYCE plcInventors: Michael Adam ZAGRODNIK, Krishnamoorthi SIVALINGAM, Satyanarayana Reddy GAJJELA, Vidor VERES-SZEKELY, Daniel LORINCZ, István ÖRÖKÖS-TÓTH, Anand Prabhu MATHIVANAN
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Publication number: 20220403790Abstract: A method of mitigating contrails produced by an aircraft having a set of gas turbine engines, comprises the steps of (i) for each engine in a first subset of the engines, reducing the operating efficiency of the engine to produce a reduction in thrust provided by that engine and (ii) for each engine in a second subset, increasing the fuel flow to the engine to increase the thrust provided by that engine, the set of at least two gas turbine engines consisting of the first and second subsets. The method provides for contrail mitigation action by means of engine operating efficiency reduction to be directed to a first subset of engines for which contrail mitigation per unit engine operating efficiency reduction is greatest, the resulting reduction in thrust provided by such engines being at least partially compensated by increasing fuel flow to engines of the second subset.Type: ApplicationFiled: June 1, 2022Publication date: December 22, 2022Applicant: ROLLS-ROYCE plcInventors: Paul FLETCHER, Peter SWANN
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Publication number: 20220402402Abstract: Aircraft with battery thermal regulation systems, including: an aircraft air inlet and an aircraft air outlet; a battery pack including battery cells; and a battery thermal regulation system including a first air channel, a surface of which is in thermal communication with the battery cells so that air flowing through the first air channel exchanges heat with the cells through the surface; and an airflow device for driving an airflow. The battery thermal regulation system has a first and a second mode operation. In the first mode, the first air channel is fluidly connected with the aircraft air inlet and the aircraft air outlet whereby, during flight of the aircraft, air can enter the aircraft through the air inlet, flow through the first air channel and exit the aircraft through the air outlet. In the second mode, the airflow device drives an airflow through the first air channel.Type: ApplicationFiled: May 23, 2022Publication date: December 22, 2022Applicant: ROLLS-ROYCE plcInventors: Michael Adam ZAGRODNIK, Krishnamoorthi SIVALINGAM, Satyanarayana Reddy GAJJELA, Vidor VERES-SZÉKELY, Daniel LORINCZ, István ÖRÖKÖS-TÓTH, Anand Prabhu MATHIVANAN, Umesh MAHAJAN, Rakesh MURALI
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Publication number: 20220403749Abstract: 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.Type: ApplicationFiled: May 19, 2022Publication date: December 22, 2022Applicant: ROLLS-ROYCE plcInventors: Crispin BOLGAR, Steven RADOMSKI
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Publication number: 20220403780Abstract: A gas turbine engine including an engine core with a duct, nacelle, and bypass duct receiving fan-accelerated bypass air flow. The core duct is located radially inside the bypass duct and receives the core air flow. A housing between the core and bypass ducts has an outer wall, which is the bypass duct inner wall, and inner wall which is core duct outer wall. The housing extends axially from the gas turbine engine, and splits fan accelerated air flow axially forward into the bypass and core ducts. At least two heat exchangers for cooling engine based oil are mounted in the housing. A flow passage inside the housing delivers air flow to the heat exchangers, and returns air flow from the heat exchangers. The at least two heat exchangers extend circumferentially, and a flow divider is between the heat exchanger ends and diverts air flow to the heat exchangers.Type: ApplicationFiled: May 19, 2022Publication date: December 22, 2022Applicant: ROLLS-ROYCE plcInventors: Harry D E PRICE, Michael I. ELLIOTT
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Publication number: 20220403980Abstract: A storage tank for liquid hydrogen comprises first and second shells each constructed of laminate material, the second shell being disposed outwardly of the first shell with respect to the centre of the storage tank. The first and second shells are mechanically connected by a first plurality of pins each of which passes through at least some layers of the second shell and at least some layers of the first shell. The storage tank may be constructed using a simpler manufacturing process involving less tooling and fewer process steps than is the case for known tanks for storing liquid hydrogen. The storage tank has also has a lower mass and reduced thermal losses compared to tanks of the prior art. The plurality of pins allows for the shells to be thinner, and hence lighter, than similar shells in tanks of the prior art.Type: ApplicationFiled: May 26, 2022Publication date: December 22, 2022Applicant: ROLLS-ROYCE plcInventor: Robert C. BACKHOUSE
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Publication number: 20220402067Abstract: A method of electron beam welding comprising splitting the output of an electron beam welder into two components, a pre/post heat ring and a fusion spot, applying the two outputs to a workpiece that is to be welded, traversing the two outputs along the desired weld path, and wherein the fusion spot lies within the pre/post heat ring and travels in tandem with and inside the pre/post heat ring. The pre/post heat ring may be annular. The fusion spot may be located at the centre of the pre/post heat ring. The output of the electron beam welder may comprise 1 to 100,000 discrete points. The beams may be deflected using the EB welder deflector coils. The time the electron beam spends on each discrete point may be identical.Type: ApplicationFiled: June 8, 2022Publication date: December 22, 2022Applicant: ROLLS-ROYCE plcInventor: Stanley G. READYHOOF
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Patent number: 11530817Abstract: A combustor including a combustor lining, a tile including a recess at an end defining a receiving surface, and a tile holder. The tile holder includes an elongate retaining head having a combustor surface configured to face a combustion chamber of a combustor, and a securing portion extending from the head, the securing portion being configured to secure the head to a combustor lining. The retaining head extends laterally with respect to an elongate direction of the retaining head to define a retaining surface laterally adjacent to the securing portion; and the retaining surface cooperates with the receiving surface of the tile to retain the tile against the combustor lining. There is also disclosed a tile holder and a tile.Type: GrantFiled: November 20, 2019Date of Patent: December 20, 2022Assignee: ROLLS-ROYCE plcInventors: Luca Tentorio, Juan Carlos Roman Casado, Giacomo Di Chiaro, Jonathan Knapton, Filippo Zambon, Radu Irimia
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Patent number: 11530651Abstract: 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.Type: GrantFiled: March 2, 2021Date of Patent: December 20, 2022Assignee: Rolls-Royce PLCInventors: Christopher P. Madden, Peter Swann
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Patent number: 11532937Abstract: Electrical systems for connecting rotary electric machines with gas turbine spools are provided. One such electrical system comprises: a first rotary electric machine mechanically coupled with a first gas turbine spool and a second rotary electric machine mechanically coupled with a second gas turbine spool, each said electric machine having an identical even number N?4 of phases, each phase having a respective index n=(1, . . .Type: GrantFiled: August 25, 2020Date of Patent: December 20, 2022Assignee: ROLLS-ROYCE plcInventors: David F Brookes, Graham P Bruce, Stephen M Husband
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Patent number: 11530492Abstract: An insert fixture has a base, a plurality of mounting brackets, and a plurality of separators. The plurality of separators extends vertically from the base and includes a plurality of grid portions extending the length of the insert fixture and a plurality of divider portions, which connect to the plurality of grid portions to form a plurality of individual component holders around one of the plurality of mounting brackets. Each individual component holder has two separated grid portion sections positioned on either side of the bracket. These grid portions have two divider portions which are also separated and positioned either side of the bracket at an angle relative to the two grid portions. The individual component holder forms a cell around the mounting bracket. The insert fixture may be constructed from a molybdenum alloy, lanthanum oxide and/or titanium zirconium molybdenum.Type: GrantFiled: January 14, 2020Date of Patent: December 20, 2022Assignees: ROLLS-ROYCE plc, ROLLS-ROYCE DEUTSCHLAND LTD & CO KGInventors: Felix Biernot, Toma D Nikolov, Priyesh R Patel, Justin P M Tsang
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Patent number: 11530652Abstract: A gas turbine engine for an aircraft. The gas turbine comprises a combustor, a fuel injection system connected with a source of fuel and configured to inject fuel into the combustor, a water injection system connected with a source of water and which is configured to inject water into the combustor, and a control system. The control system is configured to identify an atmospheric condition; determine a water-fuel ratio for injection into the combustor of the gas turbine engine in response to the atmospheric condition; and control injection of fuel and water by the fuel injection system and the water injection system according to said water-fuel ratio to control an soot emissions caused by combustion of fuel therein.Type: GrantFiled: March 2, 2021Date of Patent: December 20, 2022Assignee: Rolls-Royce PLCInventors: Christopher P. Madden, Peter Swann
