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公开(公告)号：US12253000B2
公开(公告)日：2025-03-18
申请号：US17795072
申请日：2021-01-18
Applicant: Rolls-Royce Deutschland Ltd & Co KG , Rolls-Royce plc
Inventor： David Williams , Stefan Menczykalski , Stephan Uhkötter , Uwe Kracht , Wolfram Kurz-Hardjosoekatmo
Abstract: An oil system of a gas turbine engine, includes a first oil circuit and a second oil circuit. Via the oil circuits, oil is supplied to a hydraulic load of a transmission of the engine. Downstream of the load, in the region of a return of the transmission, oil is introduced into the oil circuits from the transmission. Upstream of the load, in the region of inlets, oil can be introduced into the transmission from the oil circuits. The second oil circuit includes an oil accumulator between the return and the inlet of the second oil circuit. The oil accumulator is configured such that, according to a feed pressure of the oil upstream of the inlet, oil is stored in the oil accumulator or oil stored in the oil accumulator is fed toward the inlet.
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公开(公告)号：US20250035046A1
公开(公告)日：2025-01-30
申请号：US18361075
申请日：2023-07-28
Inventor： Jeffrey Lawrence , Peter Schenk , Jacob Ward Harral , Brian Joseph Huber
Abstract: An example system includes a first gas-turbine engine configured to propel an aircraft, the first gas-turbine engine comprising: a first air-turbine starter, the first air-turbine starter configured to rotate a spool of the first gas-turbine engine; and a first electric starter, the first electric starter configured to rotate the spool of the first gas-turbine engine; and one or more controllers collectively configured to: cause, during a time period, the first-air turbine starter and the first electric starter to start the first gas-turbine engine while the aircraft is on the ground; measure, during the time period, values of one or more parameters of the first gas-turbine engine; and determine, based on the values of the one or more parameters, whether the first electric starter is available for use in performing mid-air restart of the first gas-turbine engine.
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公开(公告)号：US12209502B1
公开(公告)日：2025-01-28
申请号：US18758996
申请日：2024-06-28
Inventor： Robert W. Heeter , Daniel E. Molnar, Jr. , Jonathan M. Rivers
Abstract: A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.
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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：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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Patent Agency Ranking
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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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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99.发明授权公开(公告)号：US12018621B1
公开(公告)日：2024-06-25
申请号：US18234657
申请日：2023-08-16
Inventor： Robert W. Heeter , Daniel E. Molnar, Jr. , Michael S. Krautheim
CPC classification number: F02C9/22 , F01D17/141 , F02K3/06 , F04D29/542 , F05D2220/36 , F05D2240/12 , F05D2240/14
Abstract: A fan case assembly adapted for use with a gas turbine engine includes a case at extends circumferentially at least partway about an axis of the gas turbine engine and a plurality of vanes. The case is formed to define a channel that extends circumferentially at least partway about the axis. The plurality of vanes are arranged in the channel and spaced apart circumferentially about the axis.
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公开(公告)号：US11970985B1
公开(公告)日：2024-04-30
申请号：US18234654
申请日：2023-08-16
Inventor： Robert W. Heeter , Daniel E. Molnar, Jr. , Jonathan M. Rivers , Michael S. Krautheim
CPC classification number: F02C9/22 , F01D17/141 , F04D29/526 , F04D29/542 , F04D29/68
Abstract: A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.
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