Patents by Inventor ROLLS-ROYCE PLC
ROLLS-ROYCE PLC has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Publication number: 20140208768Abstract: A cooling system for a gas turbine engine (10) having a compressor (14), a combustor (16) and a turbine section arranged to receive combustion products from the combustor. The cooling system includes ducting (32,44) defining a flow path from the compressor to a component, such as a turbine blade (26) to be cooled within the turbine section. The ducting (32) bypasses the combustor (16). A heat exchanger (34) may be arranged in the flow path to extract heat from the flow between the compressor and the component. One or more valves (36;64;66) in the flow path are actuated under the control of a controller (48;60) at a predetermined frequency of actuation so as to pulse the flow between the heat exchanger and the component, typically to improve the aerodynamic efficiency of turbine blades in use.Type: ApplicationFiled: December 19, 2012Publication date: July 31, 2014Applicant: ROLLS-ROYCE PLCInventor: ROLLS-ROYCE PLC
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Publication number: 20140141174Abstract: A method of manufacturing a thermal barrier coated article including: forming an article having a first and second surface, the article having projections extending from the first surface away from the first and second surface, each projection having a first end adjacent the first surface and a second end remote from the first surface, each projection having a blind passage extending therethrough from the second surface through the article towards the second end of the projection, the blind passage in the projection being closed at the second end of the projection, depositing a thermal barrier coating on the first surface around each of the projections and on the second ends, removing the thermal barrier coating from the second ends, and removing the second end of each projection to form a passage through the projection extending from the second surface through the article to the second end of the projection.Type: ApplicationFiled: March 13, 2013Publication date: May 22, 2014Applicant: ROLLS-ROYCE PLCInventor: ROLLS-ROYCE PLC
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Publication number: 20140140860Abstract: An aerofoil component of a gas turbine engine is provided. The component has a longitudinally extending aerofoil portion which spans, in use, a working gas annulus of the engine. The aerofoil portion contains an internal chamber for a flow of coolant. The chamber includes a helical passage which spirals in a plurality of turns around an axis that extends in the length direction of the aerofoil portion.Type: ApplicationFiled: January 4, 2013Publication date: May 22, 2014Applicant: ROLLS-ROYCE PLCInventor: ROLLS-ROYCE PLC
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Publication number: 20140072426Abstract: A turbomachine casing assembly includes a first casing element locatable radially outward of one or more rotating aerofoil elements of a turbomachine, a second casing element located radially distal to the first casing element. A void is provided between a radially proximal face of the first casing element and a radially proximal face of the second casing element, at the first end of the first casing element. The first end of the first casing element is located against a corresponding first end of the second casing element by an energy absorbing element, with the first casing element; including a cantilever. The cantilever is arranged in a region extending along the first casing element from the first end; and having a pivot axis at a mid portion thereof.Type: ApplicationFiled: January 15, 2013Publication date: March 13, 2014Applicant: ROLLS-ROYCE PLCInventor: ROLLS-ROYCE PLC
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Publication number: 20140064949Abstract: A turbomachine casing assembly includes a first casing element locatable radially outward of one or more rotating aerofoil elements of a turbomachine and a second casing element located radially distal to the first casing element. A void is provided between a radially proximal face of the first casing element and a radially proximal face of the second casing element, at the first end of the first casing element. The first end of the first casing element is located against a corresponding first end of the second casing element by an energy absorbing element, with the first casing element; including a cantilever. Release of one of the rotating aerofoil elements results in the element, or part thereof, impacting the first casing element which results in the cantilever bending into the void provided between the first and second casing elements.Type: ApplicationFiled: January 15, 2013Publication date: March 6, 2014Applicant: ROLLS-ROYCE PLCInventor: ROLLS-ROYCE PLC
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Publication number: 20140064967Abstract: An aerofoil typically for a blade or vane for a gas turbine engine comprises a pressure wall, a suction wall and a web that extends therebetween. One of the walls comprises an inner leaf and an outer leaf which defines a cavity, the other wall defines a first outlet, the aerofoil defines at least one first passage extending from the cavity through the web and to the outlet. Coolant in the cavity on one side wall of the aerofoil is thereby routed across the web to be used to cool the other wall by convention and formation of a coolant film.Type: ApplicationFiled: November 20, 2012Publication date: March 6, 2014Applicant: ROLLS-ROYCE PLCInventor: ROLLS-ROYCE PLC
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Publication number: 20130336781Abstract: An aircraft includes a propulsive fan arrangement having an intake and an exhaust. The fan arrangement is mounted adjacent a gas washed surface of the aircraft in the form of a suction surface of a wing. The intake is separated from the suction surface to define a channel therebetween. The aircraft further includes a Venturi device positioned downstream of the fan exhaust to draw boundary layer air through the channel.Type: ApplicationFiled: November 8, 2012Publication date: December 19, 2013Applicant: ROLLS-ROYCE PLCInventor: ROLLS-ROYCE PLC
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Publication number: 20130336761Abstract: A turbomachine casing assembly includes a first casing element locatable radially outward of one or more rotating aerofoil elements of a turbomachine, a second casing element located radially distal to the first casing element and one or more arcuate fence elements positioned between the first and second casing elements. Following impact of a detached fan blade, a radially outward movement of the first casing element causes the or each fence element to project into the air flow passing through the turbomachine.Type: ApplicationFiled: October 25, 2012Publication date: December 19, 2013Applicant: ROLLS-ROYCE PLCInventor: ROLLS-ROYCE PLC
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Publication number: 20130306024Abstract: The invention relates to a duct for a vehicle, comprising: an elongate passageway defined by at least one wall, the passageway having first and second ends relative to the longitudinal axis of the passageway; a non-annular inlet at the first end of the passageway for receiving a first fluid flow from the boundary layer of the vehicle when in use; and, an annular outlet at the second end of the passageway having an radially inner circumferential wall and a radially outer circumferential wall, the annular outlet being in fluid communication with a propulsive unit when in use, wherein the radially inner and outer circumferential walls extend continuously to the inlet.Type: ApplicationFiled: September 27, 2012Publication date: November 21, 2013Applicant: ROLLS-ROYCE PLCInventor: ROLLS-ROYCE PLC
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Publication number: 20130266447Abstract: A rotor assembly for a gas turbine engine, the rotor assembly has a disc supporting a plurality of radially extending blades. The blades define passages therebetween and each passage has an annulus filler assembly. The annulus filler assembly includes at least two bodies and a brace, each of the bodies being arranged to abut respective adjacent blades and the brace is arranged to occupy a position centrally of the two bodies. The brace is mounted to the disc and each body and the brace are arranged to engage one another to form an airwash surface. The airwash surface improves aerodynamic flow of air entering the gas turbine engine.Type: ApplicationFiled: November 1, 2012Publication date: October 10, 2013Applicant: ROLLS-ROYCE PLCInventor: ROLLS-ROYCE PLC
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Publication number: 20130266419Abstract: Intakes of gas turbine engines are subject to cross winds and high incidence cross flows which can affect the stability of air to the propulsive fan. An active flow control arrangement for an intake comprises a compressed gas supply pipe, a valve arrangement, a controller, and a compressed gas distribution pipe. The supply pipe is fluidly connects between a compressed gas source and the valve arrangement. The distribution pipe fluidly connects between the valve arrangement and intake surface for supply of compressed gas thereto. The active flow control arrangement is operable to supply compressed gas to the intake surface to prevent separation of a main air flow passing through the intake from the inlet surface thereby maintaining stability of the intake air flow to the fan.Type: ApplicationFiled: December 13, 2012Publication date: October 10, 2013Applicant: ROLLS-ROYCE PLCInventor: ROLLS-ROYCE PLC
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Publication number: 20130263601Abstract: A gas turbine engine having a rotational axis, an intake and a compressed gas source; the intake includes a lining having a facing which defines an inlet surface and an array of holes; the array of holes includes at least a first set of holes and a second set of holes, the holes of the first set of holes are angled a relative to a radial line and the holes of the second set of holes are angled ? relative to the radial line; the angles ? and ? are different. An active flow control arrangement including a compressed gas supply pipe, a valve arrangement, a controller, a compressed gas distribution pipe may be provided. Compressed gas may be provided to prevent the formation of separation of a main gas flow through the intake and prevent or remove ice accretion.Type: ApplicationFiled: December 13, 2012Publication date: October 10, 2013Applicant: ROLLS-ROYCE PLCInventor: ROLLS-ROYCE PLC
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Publication number: 20130264110Abstract: An electrical assembly including electrical raft having electrical conductors embedded in a rigid material is provided. The electrical assembly has an electrically conductive screen layer. The electrically conductive screen layer provides electromagnetic protection to the electrical conductors. The electrically conductive screen layer is electrically connected to a mounting fixture, which in turn may be electrically connected to an apparatus on which the electrical assembly may be mounted. The electrical raft is used to transport electrical signals (which may be, for example power and/or control signals), for example around a gas turbine engine.Type: ApplicationFiled: December 17, 2012Publication date: October 10, 2013Applicant: ROLLS-ROYCE PLCInventor: ROLLS-ROYCE PLC
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Publication number: 20130224029Abstract: A balanced rotor comprising a circumferential slot and a plurality of aerofoils each secured in the slot by a respective root, the root having a root block having circumferentially facing flanks and a seal wing extending circumferentially from one of the flanks, characterised in that the seal wing has a notch engaging a balance weight positioned between adjacent roots.Type: ApplicationFiled: January 28, 2013Publication date: August 29, 2013Applicant: ROLLS-ROYCE PLCInventor: ROLLS-ROYCE PLC
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Publication number: 20130219914Abstract: A fuel conditioning apparatus for de-oxygenating a liquid hydrocarbon fuel has a catalyst portion which, in turn, has an inlet portion and an outlet portion. A hydrocarbon fuel stream is fed through the inlet portion and into the catalyst portion where it passes over a catalytically active component. The catalytically active component promotes the reaction of the fuel with the dissolved oxygen in the fuel stream, converting it into less chemically reactive forms and thereby reducing the fuel's propensity to form carbonaceous deposits.Type: ApplicationFiled: February 20, 2013Publication date: August 29, 2013Applicant: ROLLS-ROYCE PLCInventor: ROLLS-ROYCE PLC
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Publication number: 20130226518Abstract: A method of determining blade tip timing measurement uncertainty comprising measuring time of arrival of each of a set of blades at each of a reference set of stationary probes. A reference blade tip parameter is derived from the measurements and the position of each of the probes. A reference condition number is calculated from the position of each of the probes and each targeted engine order, and then a mean calculated. Combinations of fewer probes are determined. For each combination, a condition number is calculated and then a mean condition number is calculated. The combination means are ordered relative to the reference mean and a predetermined number of combinations are selected. A blade tip parameter is derived for the selected combinations. Finally uncertainty of the blade tip parameter for each selected combination is calculated as a percentage of the reference blade tip parameter.Type: ApplicationFiled: January 23, 2013Publication date: August 29, 2013Applicant: ROLLS-ROYCE PLCInventor: ROLLS-ROYCE PLC
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Publication number: 20130216364Abstract: An aircraft propulsion system has an engine assembly having an axis of rotation, a fan assembly operatively connected to the engine assembly and comprising a plurality of fan blades arranged circumferentially around the axis of rotation and a monolithic nacelle assembly which circumferentially encloses the fan assembly. The propulsion system has a ratio of fan assembly outer diameter to nacelle assembly outer diameter of at least 0.87. As a result, the propulsion system provides for a significantly larger fan assembly outer diameter for a given nacelle assembly outer diameter than a conventional prior art turbofan engine, thereby increasing the specific power output or the bypass ratio of the propulsion system, which will result in improved propulsive efficiency without an increase in nacelle drag.Type: ApplicationFiled: February 13, 2013Publication date: August 22, 2013Applicant: ROLLS-ROYCE PLCInventor: ROLLS-ROYCE PLC
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Publication number: 20130210572Abstract: This invention relates to a unison ring assembly, comprising: a first unison ring and a second unison ring concentrically aligned along a principal axis, the first and second rings being rotatable about the principal axis; and, a gear mechanism for simultaneously rotating the first and second unison rings about the principal axis.Type: ApplicationFiled: February 7, 2013Publication date: August 15, 2013Applicant: ROLLS-ROYCE PLCInventor: ROLLS-ROYCE PLC
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Publication number: 20130200569Abstract: A leaf seal effects a seal between two, coaxial, relatively rotating components. The leaf seal has an annular pack of stacked leaves or a plurality of axially arranged annular packs of stacked leaves. The or each pack is mountable to one of the components with its leaves extending towards the other component such that the leaf edges of the pack are presented for wiping contact with the other component. The leaf seal further has upstream and downstream coverplates at the respective axial ends of the seal. Each coverplate is spaced from the adjacent annular pack by a respective axial gap. When viewed in the axial direction, each coverplate covers at least a portion of the radial extent of the adjacent pack. The upstream and/or the downstream coverplate is flexible to axially deflect under differential pressures which the seal experiences in operation.Type: ApplicationFiled: January 31, 2013Publication date: August 8, 2013Applicant: ROLLS-ROYCE PLCInventor: ROLLS-ROYCE PLC
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Publication number: 20130199194Abstract: A combustor head arrangement including a heatshield including an aperture therethrough. A meter panel having a cold side and a hot side, an aperture and a slot. At least one of the meter panel and the heatshield has a retaining feature on the cold side; one of the meter panel and the heatshield has an anti-rotation feature. The arrangement includes a burner seal sized to fit through the aperture in the meter panel from the hot side towards the cold side. The burner seal has a tang configured to pass through the slot when the burner seal is in a first orientation and to be retained by the retaining feature and the anti-rotation feature when the burner seal is rotated to a second orientation. Also a method of assembling the combustor head.Type: ApplicationFiled: December 4, 2012Publication date: August 8, 2013Applicant: ROLLS-ROYCE PLCInventor: ROLLS-ROYCE PLC