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公开(公告)号：US11204037B2
公开(公告)日：2021-12-21
申请号：US17338159
申请日：2021-06-03
Applicant: ROLLS-ROYCE plc
Inventor： Richard G Stretton , Michael C Willmot
Abstract: A gas turbine engine for an aircraft includes an engine core including an engine core, a turbine, a compressor, and a core shaft connecting the turbine to the compressor, the turbine comprising a lowest pressure rotor stage, the turbine having a turbine diameter at the lowest pressure rotor stage. A fan located upstream of the engine core, the fan comprising a plurality of fan blades extending from a hub, the hub and fan blades together defining a fan face having a fan face area and a fan tip radius. A ratio of the fan tip radius to the turbine diameter at the lowest pressure rotor stage is in the range from 1.2 to 2.0.
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公开(公告)号：US20210388726A1
公开(公告)日：2021-12-16
申请号：US17286327
申请日：2019-09-30
Applicant: Rolls-Royce plc
Inventor： David Churcher , Andrew R. Collis
Abstract: A method of manufacturing a component for a gas turbine engine includes applying a thermoplastic polymer sheet over a composite body for the component; applying a shield over part of the composite body, the shield terminating at an end which overlies the thermoplastic polymer sheet and defines an interface between shielded and unshielded regions of the component; and pressing the shield into the thermoplastic polymer sheet so that the thermoplastic polymer sheet deforms around the end of the shield, such that the exterior profile of the component at the interface between the shielded and unshielded regions is flush.
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公开(公告)号：US20210381430A1
公开(公告)日：2021-12-09
申请号：US17331020
申请日：2021-05-26
Applicant: ROLLS-ROYCE PLC
Inventor： Matthew SILVESTER , Geoffrey HUGHES
Abstract: A gas turbine engine for an aircraft includes a fan system having a reverse travelling wave first flap mode, Fan RTW, and including a fan located upstream of the engine core; a fan shaft; and a front engine structure arranged to support the fan shaft and having a front engine structure nodding mode comprising a pair of modes at similar, but not equal, natural frequencies in orthogonal directions; and a gearbox. An LP rotor system including the fan system and a gearbox output shaft arranged to drive the fan shaft has a first reverse whirl rotor dynamic mode, Rotor RW, and a first forward whirl rotor dynamic mode, 1FW. The engine has a maximum take-off speed, MTO. A backward whirl frequency margin of: the lowest frequency of either mode Fan RTW or Rotor RW at the MTO speed the MTO speed may be in the range from 15 to 50%.
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公开(公告)号：US11196320B2
公开(公告)日：2021-12-07
申请号：US16690510
申请日：2019-11-21
Applicant: Rolls-Royce plc , Rolls-Royce Corporation
Inventor： Mark Boden , Donald Klemen , Jonathan Terrell , Brian Maners
Abstract: A rotor of an electric machine includes a main rotor body having a longitudinal axis, the main rotor body comprising: a hollow cylinder body with a first end and a second end; an integral end flange at the first end; a separate end flange disposed at the second end of the cylinder body; and laminations disposed on an outer surface of the cylinder body, the laminations comprising magnetic material.
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公开(公告)号：US11193381B2
公开(公告)日：2021-12-07
申请号：US16415196
申请日：2019-05-17
Applicant: Rolls-Royce plc
Inventor： Michael J. Whittle
Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes a spar, a turbine vane, and load transfer pins. The spar comprises metallic materials and is configured to support other components of the turbine vane assembly relative to an associated turbine case. The turbine vane comprises ceramic matrix composite materials and is shaped to include an airfoil configured to direct the flow of hot gasses through a primary gas path of the turbine vane assembly.
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Patent Agency Ranking
公开(公告)号：US11189398B2
公开(公告)日：2021-11-30
申请号：US16734491
申请日：2020-01-06
Applicant: ROLLS-ROYCE plc
Inventor： Chloe J. Palmer
Abstract: A superconducting electrical power distribution system has a superconducting bus bar and one or more bus bar thermal conductor lines extending in thermal proximity along the bus bar to receive heat from the bus bar over the length of the bus bar. The system further has superconducting cables electrically connected to the bus bar at respective electrical joints distributed along the bus bar. The system further has a cryogenic cooling sub-system. The system further has a network comprising first and second thermal conductor lines, each line comprising a cold end which is cooled by the cryogenic cooling sub-system, and an opposite hot end, whereby heat received by each line is normally conducted along the line in a direction from its hot end to its cold end.
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公开(公告)号：US11181042B2
公开(公告)日：2021-11-23
申请号：US16411347
申请日：2019-05-14
Applicant: ROLLS-ROYCE plc
Inventor： Michael O Hales , Craig W Bemment , Stephane M M Baralon , Benjamin J Sellers , Christopher Benson , Benedict R Phelps , Mark J Wilson
Abstract: A gas turbine engine has a cycle operability parameter β in a defined range to achieve improved overall performance, taking into account fan operability and/or bird strike requirements as well as engine efficiency. The defined range of cycle operability parameter β may be particularly beneficial for gas turbine engines in which the fan is driven by a turbine through a gearbox.
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公开(公告)号：US20210355843A1
公开(公告)日：2021-11-18
申请号：US17231460
申请日：2021-04-15
Applicant: ROLLS-ROYCE plc
Inventor： Fernando L. TEJERO EMBUENA , David G. MACMANUS , Christopher TJ. SHEAF
IPC: F01D25/24
Abstract: A nacelle for a gas turbine engine includes a leading edge, a trailing edge and a longitudinal centre line along a length of the nacelle. A highlight radius (rhi) is defined as a radial distance between the longitudinal centre line and the leading edge. A trailing edge radius (rte) is defined as a radial distance between the longitudinal centre line and the trailing edge. A nacelle length (Lnac) is defined as an axial distance between the leading edge and the trailing edge. A ratio between the nacelle length (Lnac) and the highlight radius (rhi) is defined as R1 (Lnac/rhi). The ratio R1 is greater than or equal to 2.4 and less than or equal to 3.2. A ratio between the trailing edge radius (rte) and the highlight radius (rhi) is defined as R2. The ratio R2 is greater than or equal to 0.89 and less than or equal to 1.
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公开(公告)号：US20210347008A1
公开(公告)日：2021-11-11
申请号：US17220318
申请日：2021-04-01
Applicant: ROLLS-ROYCE plc
Inventor： Karl S. HUCKERBY
Abstract: A method of machining a surface of a component. The method comprises scanning the surface of the component to obtain scanned electronic 3D data representing the scanned surface of the component locating a surface defect of the scanned surface and identifying a defect region that surrounds and includes the surface defect, and providing electronic 3D data representing a patch having the desired shape of the defect region. The method also comprises transforming the patch to generate a tooling path for repairing the surface defect. The transformation comprising translating a plurality of nodes of the patch. The translation distance of each node based on the distance of that node from an origin node of the patch. The method further comprises machining the surface of the component according to the generated tooling path.
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公开(公告)号：US20210346952A1
公开(公告)日：2021-11-11
申请号：US17179526
申请日：2021-02-19
Applicant: Rolls Royce plc
Inventor： Gary R. JONES , John L. SULLEY , Edward D. WARNER
Abstract: A method of fabricating a component is described and involves retaining a canister as an integral part of the component after performing an isostatic pressing process. The method comprises: providing a canister having a canister wall that encloses an internal cavity, the canister wall comprising at least a first wall section and a second wall section, where the first wall section and the second wall section are of different materials; filling the internal cavity with a powdered material; performing an isostatic pressing process on the filled canister to consolidate the powder; and retaining the canister as an integral part of the component such that an internal structure of the component comprises the consolidated powder and the canister wall forms at least part of a surface of the component that covers the internal structure.
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