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公开(公告)号：US11098656B2
公开(公告)日：2021-08-24
申请号：US17062272
申请日：2020-10-02
Applicant: ROLLS-ROYCE PLC
Inventor： Mark Spruce
Abstract: A gas turbine engine for an aircraft has an engine core having a turbine, compressor, and core shaft connecting the turbine and compressor; a fan upstream the engine core, the fan having fan blades; and a gearbox. The gearbox receives an input from a core shaft and outputs drive to a fan to drive the fan at a lower rotational speed than the core shaft. The gearbox is an epicyclic gearbox and has a sun gear, planet gears, ring gear, and planet carrier on which the planet gears are mounted. The gearbox has a gear mesh stiffness between the planet gears and the ring gear and a gear mesh stiffness between the planet gears and the sun gear. The gear mesh stiffness between the planet gears and the ring gear divided by that between the planet gears and the sun gear is in the range from 0.90 to 1.28.
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公开(公告)号：US20210254501A1
公开(公告)日：2021-08-19
申请号：US17235234
申请日：2021-04-20
Applicant: ROLLS-ROYCE PLC
Inventor： Ian J BOUSFIELD , Duncan A MACDOUGALL
Abstract: A gas turbine engine includes a fan mounted to rotate about a main longitudinal axis; an engine core, including a compressor, a combustor, and turbine coupled to the compressor through a shaft; and reduction gearbox; wherein the compressor includes a plurality of stages, each stage including a respective rotor and stator, a first stage of the plurality of stages being arranged at an inlet and including a first rotor with a plurality of blades; each blade extending chordwise from a leading edge to a trailing edge, and from root to tip for a span height, wherein 0% of the span height corresponds to the root and 100% of span height corresponds to tip; wherein a ratio of a leading edge radius of each of the plurality of first rotor blades at 0% span height to a minimum leading edge radius is comprised between 1 and 1.50.
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公开(公告)号：US20210254489A1
公开(公告)日：2021-08-19
申请号：US17100388
申请日：2020-11-20
Applicant: ROLLS-ROYCE plc , ROLLS-ROYCE Corporation
Inventor： Simon J. Donovan , Peter E. Daum , Christopher P. Heason
IPC: F01D11/12 , B23K26/00 , B23K26/08 , B23K26/144 , B23K26/342 , B33Y10/00 , B33Y50/02 , C22C19/05 , B33Y80/00
Abstract: A method of forming a wall structure on a substrate comprises depositing, by additive-layer, powder-fed, laser-weld deposition apparatus, a plurality of material layers overlying one another on the substrate to form the wall structure. Each material layer of the plurality of material layers has (a) a layer thickness, measured in a direction locally perpendicular to a profile of the substrate, of no greater than about 350 μm and (b) a layer width, measured in a direction locally parallel to the profile of the substrate, of no greater than about 1200 μm.
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公开(公告)号：US20210246811A1
公开(公告)日：2021-08-12
申请号：US17169624
申请日：2021-02-08
Applicant: ROLLS-ROYCE plc
Inventor： Alan R. MAGUIRE , Richard SHARPE , Neil J. DAVIES
Abstract: A system for supplying lubricant to a component of a gas turbine engine having a fan shaft is provided. The system includes a pump drivably couplable to the fan shaft for pumping lubricant to the component. The pump includes an inlet for receiving lubricant from a lubricant source, an outlet for outputting lubricant to the component and a swashplate movable between at least a first position and a second position. The system also includes a swashplate actuator for actuating the swashplate between the first position and the second position according to whether the fan shaft is rotating in a forward direction or a reverse direction opposite to the forward direction.
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公开(公告)号：US11085643B2
公开(公告)日：2021-08-10
申请号：US16254705
申请日：2019-01-23
Applicant: ROLLS-ROYCE plc
Inventor： Richard Freeman , Christopher Rafferty , Thomas Jones , Matthew Murphy , Nicholas M. Brown
IPC: F23R3/14 , F23R3/28 , F23D14/00 , F23R3/10 , F23D11/00 , F23D11/38 , F23C7/00 , F23M5/08 , B33Y10/00 , B33Y80/00 , B29C64/153 , B01F5/00 , B01F15/00 , F23R3/46
Abstract: An air swirler arrangement comprises a coaxial arrangement of an inner and an outer air swirler passage. Each air swirler passage comprises a radial flow swirler. Air swirler arrangement comprises a coaxial arrangement of first, second and third members. Second member has radially extending upstream portion spaced axially from first member and a convergent portion. Third member has a radially extending upstream portion spaced axially from the upstream portion of second member and a radially inner surface having convergent and divergent downstream portions and a radially outer surface having a divergent downstream portion. First, second and third members the vanes of the radial flow swirlers is a monolithic structure. Plurality of circumferentially spaced passages are provided within the third member and each passage has an inlet in the surface and an outlet arranged to direct fluid onto the divergent portion of the surface or the surface of the third member.
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Patent Agency Ranking
公开(公告)号：US20210222880A1
公开(公告)日：2021-07-22
申请号：US17149266
申请日：2021-01-14
Applicant: Rolls-Royce plc
Inventor： Stephen C. Harding , Frederic Witham
Abstract: A combustion chamber (15) comprising a wall at least partially defining a combustion zone and having a first surface (41) facing away from the combustion zone and a second surface (43) facing the combustion zone, the wall having at least one effusion cooling aperture (69, 73) extending there-through from the first surface to the second surface, the effusion cooling aperture having an inlet in the first surface and an outlet in the second surface, the first surface having a particle separator (84) at least partially located upstream of the inlet of the effusion cooling aperture, the particle separator projecting away from the first surface and away from the combustion zone.
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公开(公告)号：US20210222632A1
公开(公告)日：2021-07-22
申请号：US17143629
申请日：2021-01-07
Applicant: ROLLS-ROYCE PLC
Inventor： Craig W. BEMMENT , Pascal DUNNING
Abstract: A gas turbine engine comprises a fan, a compressor, a low pressure turbine and a high pressure turbine. The fan diameter is greater than 250 cm and less than 381 cm; and the gas turbine engine has a first thrust at sea level static conditions and a second thrust at end of runway conditions; and a thrust take-off ratio greater than 1.32; wherein the thrust take-off ratio is the ratio of the first thrust to the second thrust.
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公开(公告)号：US20210222630A1
公开(公告)日：2021-07-22
申请号：US17061002
申请日：2020-10-01
Inventor： Mark D. TAYLOR , Erik JANKE , Rory D. STIEGER , Daniel SWAIN
Abstract: A turboshaft gas turbine engine comprises, in fluid flow series, a gas-generator compressor, a combustor, a gas-generator turbine, and a free power turbine. The gas-generator turbine is a single stage turbine having a specific work of from 200 to 350 kilojoules per kilogram, said specific work being the power output of the turbine per unit mass flow therethrough.
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公开(公告)号：US11063527B2
公开(公告)日：2021-07-13
申请号：US16570739
申请日：2019-09-13
Applicant: ROLLS-ROYCE plc
Inventor： David R. Trainer , Ellis F H Chong , Zhigang Sun
Abstract: An electrical converter (203) having an active diode-clamped multilevel topology is shown. Each clamping diode is connected in antiparallel with a switch (S5A, S5B). The converter comprises polyphase supply phases (A, B, C) each of which are connected via a respective phase leg (401, 402, 403) to dc rails (301, 302) and a dc-link capacitor. The dc-link capacitor includes a plurality of series-connected capacitors (404, 405). A controller is configured to, in response to an event signal, for each phase leg, activate a combination of switches therein to form a pair of parallel conduction paths to a midpoint (406) between two capacitors in the dc-link capacitor, thereby connecting each phase to the same node.
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公开(公告)号：US11059240B2
公开(公告)日：2021-07-13
申请号：US15768402
申请日：2016-10-13
Applicant: ROLLS-ROYCE PLC
Inventor： Ashley Barnes , Darren Ivor James
IPC: B29C70/38 , G05B19/4097 , B29C33/38 , B29C70/54
Abstract: Methods of designing a plybook for a composite component are disclosed. Included method comprising: defining a component volume corresponding to the composite component to be manufactured; defining a plurality of successive plies of composite material to fill the component volume; simulating at least some of the plurality of successive plies of composite material based on an estimate of variable cured ply thickness, wherein the variable cured ply thickness is estimated by: simulating at least a portion of a respective ply of composite material; and estimating a cured ply thickness for the portion of composite material at least partly based on local conditions of the portion. A plybook is defined based on the plurality of simulated plies.
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