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公开(公告)号：US20200173456A1
公开(公告)日：2020-06-04
申请号：US16398870
申请日：2019-04-30
Applicant: ROLLS-ROYCE plc
Inventor： Clive BREEN
Abstract: A gas turbine engine for an aircraft, includes: an engine core having a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan assembly located upstream of the engine core; and a gearbox receiving an input from the core shaft and outputs drive to the fan assembly so as to drive the fan assembly at a lower rotational speed than the core shaft, wherein the fan assembly has fan blades mounted around a hub, the fan blades having blade tips defining an outer diameter of the fan assembly of from around 220 cm to around 400 cm, the hub having slots located around a rim of the hub, each slot receiving a root of a corresponding fan blade, wherein a ratio of a mass of the hub to a total mass of the fan blades is within the range of around 0.45 to around 0.7.
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402.发明申请公开(公告)号：US20200173368A1
公开(公告)日：2020-06-04
申请号：US16679576
申请日：2019-11-11
Applicant: ROLLS-ROYCE plc
Inventor： Stephen M. HUSBAND , Ahmed M Y RAZAK , Paul R. MILLER
Abstract: A method of controlling at least part of a start-up or re-light process of a gas turbine engine, the method comprising: controlling ignition within a combustion chamber of the gas turbine engine; controlling rotation of a low pressure compressor using a first electrical machine, and controlling rotation of a high pressure compressor using a second electrical machine, the combustion chamber downstream of the low pressure compressor and high pressure compressor; determining if an exit pressure of the high pressure compressor is equal to or greater than a self-sustaining threshold pressure; and in response to determining that the exit pressure of the high pressure compressor is equal to or greater than the self-sustaining threshold pressure, ceasing controlling rotation of the low pressure compressor using the first electrical machine, and/or the high pressure compressor using a second electrical machine.
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公开(公告)号：US20200165978A1
公开(公告)日：2020-05-28
申请号：US16678210
申请日：2019-11-08
Applicant: ROLLS-ROYCE plc
Inventor： Salwan D. SADDAWI
Abstract: An aerofoil and an aerofoil assembly, in particular an aerofoil with improved stagnation zone cooling and an aerofoil assembly comprising such an aerofoil. The aerofoil is an aerofoil for a gas turbine engine comprising a pressure surface, a suction surface, a leading edge, a trailing edge, a stagnation zone located in the region of the leading edge, and an elongate channel running along the leading edge at the stagnation zone.
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公开(公告)号：US10662895B2
公开(公告)日：2020-05-26
申请号：US15593674
申请日：2017-05-12
Applicant: ROLLS-ROYCE plc
Inventor： John R Wells
Abstract: A fan nacelle for an aircraft gas turbine engine. The nacelle includes an aft nacelle portion including a radially outer surface and a radially inner surface, the radially outer and inner surfaces defining an internal cavity therebetween. The nacelle further includes an aft nacelle segment translatable along a translation vector having an axial component, wherein the aft nacelle segment is configured to translate between a forward deployed position in which the nacelle defines a first primary fan nozzle exit area (A1) and a clean position in which the nacelle defines a second primary fan nozzle exit area (A2) less than the first primary fan nozzle exit area A1, wherein in the forward deployed position, the aft nacelle segment is at least partly located within the internal cavity.
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公开(公告)号：US10662809B2
公开(公告)日：2020-05-26
申请号：US15945753
申请日：2018-04-05
Applicant: ROLLS-ROYCE plc
Inventor： Simon Pitt
Abstract: A vane cooling system for a gas turbine engine comprises a vane (21) arranged on a stator and having a chamber (23) extending continuously from a radially inner end to a radially outer end of the vane. The vane (21) has; a radially inner inlet (24) and a radially outer inlet (25), a first cooling fluid feed (39) in communication with the radially inner inlet (24) and a second cooling fluid feed (28) in communication with the radially outer inlet (25), The first cooling fluid feed (39) has a higher pressure than the second cooling feed (28). A flow adjustment device (30) is arranged for adjusting a flow of the second cooling fluid feed into the radially outer inlet (25).
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Patent Agency Ranking
公开(公告)号：US10662803B2
公开(公告)日：2020-05-26
申请号：US15458154
申请日：2017-03-14
Applicant: ROLLS-ROYCE PLC
Inventor： Matthew Mears
Abstract: An aerofoil body for a gas turbine engine is provided. The aerofoil body has leading and trailing edge portions, wherein one of the leading and trailing edge portions is a morphable edge portion having a composite layer structure. The aerofoil body further has a non-morphing central portion which forms pressure and suction surfaces of the aerofoil body between the leading and trailing edge portions. The composite layer structure includes a return spring, one or more shape memory alloy layers, and a flexible cover for the return spring and the one or more shape memory alloy layers. The flexible cover defines pressure and suction surfaces of the aerofoil body at the morphable edge portion. The one or more shape memory alloy layers are electrically heatable to deform the layers against the resistance of the return spring, and thereby alter the pitch of the aerofoil body at the morphable edge portion.
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公开(公告)号：US20200156202A1
公开(公告)日：2020-05-21
申请号：US16663393
申请日：2019-10-25
Applicant: ROLLS-ROYCE plc
Inventor： Sufyan N. KHAN , David T. CURTIS
Abstract: Method of reducing the thickness of a bore of a cylindrical workpiece for use as a gear. The method involves the steps of: mounting a cylindrical workpiece having a horizontal central axis and an outer diameter in a grinding machine; and grinding the bore of the cylindrical workpiece to reduce its thickness using a grinding wheel that has a diameter that is from 40% to 80% of the outer diameter of the cylindrical bore and has a direction of rotation about an axis of rotation that is parallel to the horizontal central axis of the cylindrical workpiece. The axis of rotation of the grinding wheel may be located from 90 degrees to 180 degrees, in the direction of rotation of the grinding wheel, from a plane that extends vertically through the workpiece when it is mounted in the grinding machine. The gear may be one of a planetary, sun, parallel axis or helical gear.
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公开(公告)号：US20200149470A1
公开(公告)日：2020-05-14
申请号：US16672592
申请日：2019-11-04
Applicant: ROLLS-ROYCE plc
Inventor： Peter A. EVANS
Abstract: A compressor stage comprising a pair of bladed discs spaced apart from one another having a plurality of bleed tubes located in the space between the bladed discs. Each bleed tube has an internal and an external surface extending radially from an inter-disc cavity at the radially innermost section of the tube to a rim of the bladed discs at radially outermost section of the tube. The bleed tubes are positioned between the bladed discs, such that the bleed tubes remove a portion of air passing through the compressor stage and direct it to an area within the inter-disc spacing. The geometric shape of the internal bore of each of the bleed tubes changes along its lengths. The cross-section of each of the bleed tubes may have a cross sectional area that changes from a substantially non-polygonal shape at the radially outermost end to a substantially polygonal shape at the radially innermost end.
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公开(公告)号：US20200149400A1
公开(公告)日：2020-05-14
申请号：US16598435
申请日：2019-10-10
Applicant: ROLLS-ROYCE plc
Inventor： Christopher M. WHITHEAD
Abstract: An aerofoil blade having a root portion provided with a low friction coating layer. The low friction coating layer is affixed to the root portion by an adhesive layer. The adhesive layer has a service temperature of 125° C. or more, for example 140° C. or more.
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公开(公告)号：US10648349B2
公开(公告)日：2020-05-12
申请号：US15915200
申请日：2018-03-08
Applicant: ROLLS-ROYCE plc
Inventor： Andrew Hewitt , Ian W R Harrogate
Abstract: A method of manufacturing a coated turbine vane (34) comprises manufacturing a turbine vane (34) having a platform (44) and an aerofoil (42) extending from the platform (44), a curved transition (60) connects the platform (44) to the aerofoil (42) and a recess (64) is provided in the curved transition (60) from the platform (44) to the aerofoil (42). A bond coating (70) is deposited on the platform (44), the aerofoil (42), the curved transition (60) and the recess (64). A ceramic thermal barrier coating (72) is deposited on the platform (44), the recess (64) and the curved transition (60) by plasma spraying. The recess (64) reduces the size of the step due to the ceramic thermal barrier coating (72) and hence improves the aerodynamics of the turbine vane (34).
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