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公开(公告)号:US12194580B2
公开(公告)日:2025-01-14
申请号:US18148790
申请日:2022-12-30
Applicant: Rolls-Royce Corporation
Inventor: Joseph Peter Henderkott , Robert Frederick Proctor
Abstract: An assembly for a dual-walled component of a gas turbine engine and methods of forming and repairing a dual-walled component. The assembly includes a cold section part having an outer surface that defines a plurality of impingement apertures, a hot section part including a pre-sintered preform, the hot section part positioned over the outer surface of the cold section part, and a plurality of support structures including the pre-sintered preform, the plurality of support structures positioned between the hot section part and the cold section part, the plurality of support structures separating the hot section part from the cold section part to define at least one cooling channel therebetween.
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公开(公告)号:US12172757B2
公开(公告)日:2024-12-24
申请号:US18155351
申请日:2023-01-17
Applicant: ROLLS-ROYCE plc , Rolls-Royce Corporation
Inventor: Christopher A. Murray , Nicholas Howarth , Daniel Swain , Ian J. Bousfield
Abstract: There is provided a blower system for providing air to an airframe system, comprising a rotor configured to be mechanically coupled to a spool 440 of a gas turbine engine, wherein the rotor is configured to: in a blower mode, be driven to rotate by the spool to discharge air to an airframe discharge port for supply to an airframe system; and, in an engine drive mode, receive air from an external air source via an impingement port that is configured to direct the received air onto the rotor and thereby drive the rotor to rotate to drive the spool to.
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公开(公告)号:US20240380295A1
公开(公告)日:2024-11-14
申请号:US18314453
申请日:2023-05-09
Applicant: Rolls-Royce Corporation
Inventor: David Russell Trawick , Mathew Gregory Hill
IPC: H02K21/16 , H02K1/2789 , H02K7/12 , H02K7/18 , H02K7/20
Abstract: An example electrical machine is described that includes active segments for variable voltage generation. The electrical machine includes a drive shaft, a fixed rotor segment, an active rotor segment, and an actuator mechanism. The fixed rotor segment is coupled to the drive shaft, where the fixed rotor segment has affixed thereon first permanent magnets of alternating polarity. The active rotor segment axially is adjacent to the fixed rotor segment along the drive shaft. The active rotor segment also has affixed thereon second permanent magnets of alternating polarity. The actuator mechanism is configured to articulate the active rotor segment relative to the fixed rotor segment and thereby alter a phase of the second permanent magnets relative to the first permanent magnets in order to change a first voltage generated by the electrical machine to a second voltage generated by the electrical machine.
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公开(公告)号:US20240352872A1
公开(公告)日:2024-10-24
申请号:US18304037
申请日:2023-04-20
Inventor: Govindaraj Kalyanasamy , Peter Schenk
Abstract: An example system includes one or more heaters configured and positioned to add thermal energy to one or more portions of a gas turbine engine after the gas turbine engine was in operation, wherein the thermal energy minimizes or prevents undesired contact or seizing of a rotor of the gas turbine engine with another component of the gas turbine engine due to warping of the rotor due to uneven cooling of the gas turbine engine after the operation. The system further includes a controller configured to control operation of the one or more heaters.
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公开(公告)号:US12091368B2
公开(公告)日:2024-09-17
申请号:US16694486
申请日:2019-11-25
Applicant: Rolls-Royce Corporation
Inventor: Taylor K. Blair
CPC classification number: C04B41/5059 , C04B41/4556 , C04B41/4558 , C04B41/522 , C04B41/524 , C04B41/87 , F02C7/30 , F05D2220/32 , F05D2230/90 , F05D2300/30
Abstract: A method may include applying a layer comprising a carbon source on a surface of a substrate including silicon; applying a layer comprising silicon on the layer comprising elemental carbon; and heat treating at least the layer comprising the carbon source to cause carbon from the layer comprising the carbon source to react with at least one of silicon from the substrate or silicon from the layer comprising silicon to form silicon carbide.
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公开(公告)号:US12077479B2
公开(公告)日:2024-09-03
申请号:US16788917
申请日:2020-02-12
Applicant: Rolls-Royce Corporation , Rolls-Royce plc
Inventor: David J. Thomas , Thomas Nixon , Michael Whittle , Jeffrey Crutchfield
CPC classification number: C04B41/4584 , C04B41/4505 , C04B41/5024 , C04B41/5059 , C04B41/5066 , C04B41/52 , C04B41/87 , B32B3/08 , B32B5/06 , B32B18/00 , B32B2260/021 , B32B2262/105 , B32B2305/026 , B32B2305/80 , B32B2603/00 , C04B2235/5252 , C04B2235/6025 , C04B2235/6027 , C04B2235/614 , C04B2235/616 , C04B2235/96
Abstract: A ceramic matrix composite (CMC) component is provided that includes: a CMC body in which an environmental protection layer is completely embedded within a CMC material of the CMC body, the environmental protection layer comprising a ceramic that has a higher impact and/or environmental resistance than the CMC material. Methods for manufacturing the CMC component are also provided.
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17.
公开(公告)号:US20240287915A1
公开(公告)日:2024-08-29
申请号:US18113386
申请日:2023-02-23
Applicant: Rolls-Royce Corporation
Inventor: Aaron D. Sippel
CPC classification number: F01D25/005 , F01D11/005 , F01D11/08 , F01D11/12 , F01D11/122 , F01D25/243 , F05D2220/32 , F05D2240/55 , F05D2300/6033
Abstract: Turbine shroud structures and a method of assembling a turbine shroud into a turbine are disclosed. The method includes arranging turbine shroud segments into a full ring and inserting the full ring into a turbine case as a single unit.
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18.
公开(公告)号:US12071382B2
公开(公告)日:2024-08-27
申请号:US16726553
申请日:2019-12-24
Applicant: Rolls-Royce Corporation
Inventor: Jun Shi , Li Li , Gregory John Kenneth Harrington
CPC classification number: C04B41/009 , C04B41/0072 , C04B41/5024 , C04B41/89 , C23C4/18 , F01D5/282 , F01D5/288 , F05D2230/31 , F05D2230/40 , F05D2230/90 , F05D2300/15 , F05D2300/6033 , F05D2300/611
Abstract: In one example, a method for forming a coating system including an environmental barrier coating (EBC) and abradable coating on a substrate. The method may include depositing the EBC on a ceramic or ceramic matrix composite (CMC) substrate to form an as-deposited EBC; heat treating the as-deposited EBC following the deposition of the as-deposited EBC on the substrate to form a heat treated EBC; and subsequently depositing an abradable coating on the heat treated EBC to form an as-deposited abradable coating. The as-deposited abradable coating may be heat treated to form a heat treated abradable coating.
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公开(公告)号:US12065258B2
公开(公告)日:2024-08-20
申请号:US18101567
申请日:2023-01-25
Inventor: Robert W. Heeter , Daniel E. Molnar, Jr. , Kathryn A. Sontag , Michael G. Meyer
IPC: B64D33/02
CPC classification number: B64D33/02 , B64D2033/0226 , B64D2033/0286
Abstract: An aircraft includes a duct system configured to receive a flow of air therethrough and a gas turbine engine. The duct system includes a main duct and inlet ducts arranged fluidly upstream of the main duct so as to conduct the flow of air from the inlet ducts into the main duct. The gas turbine engine in downstream fluid communication with the main duct.
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公开(公告)号:US12025059B1
公开(公告)日:2024-07-02
申请号:US18088994
申请日:2022-12-27
Inventor: Robert W. Heeter , Daniel E. Molnar, Jr. , Kathryn A. Sontag , Michael G. Meyer
CPC classification number: F02C9/20 , F02C3/04 , F02C6/00 , F05D2220/32 , F05D2220/70 , F05D2270/05 , F05D2270/101
Abstract: A gas turbine engine comprises a primary fan and an engine core. The primary fan is mounted for rotation about an axis of the gas turbine engine to provide thrust. The engine core is coupled to the primary fan and configured to drive the primary fan about the axis to cause the fan to push air to provide thrust for the gas turbine engine.
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