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公开(公告)号：US12129043B1
公开(公告)日：2024-10-29
申请号：US18238755
申请日：2023-08-28
CPC分类号： B64D33/08 , F01M5/005 , F16K1/22 , F16K31/041
摘要： A system is provided for an aircraft. This aircraft system includes a heat exchanger, a lubricant flow circuit and a bypass valve. The lubricant flow circuit includes an inlet passage, an outlet passage, a heat exchanger passage and a bypass passage. The heat exchanger passage extends through the heat exchanger. The bypass passage bypasses the heat exchanger. The heat exchanger passage and the bypass passage are fluidly coupled in parallel between the inlet passage and the outlet passage. The bypass valve is fluidly coupled inline along the lubricant flow circuit. The bypass valve is operable to regulate lubricant flow through the bypass passage. The bypass valve includes a rotary electric motor.
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公开(公告)号：US12123839B2
公开(公告)日：2024-10-22
申请号：US17401899
申请日：2021-08-13
申请人： RTX CORPORATION
摘要： A manufacturing method is provided. During this method, a preform component for a turbine engine is provided that includes a substrate. A meter section of a cooling aperture is formed in the substrate. An external coating is applied over the substrate. At least a portion of the substrate and the external coating is scanned with an imaging system to provide scan data indicative of an internal structure of the portion of the substrate and the external coating. A diffuser section of the cooling aperture is formed in the external coating and the substrate based on the scan data.
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公开(公告)号：US12123305B2
公开(公告)日：2024-10-22
申请号：US17993517
申请日：2022-11-23
CPC分类号： F01D11/003 , F01D5/025 , F01D5/30 , F05D2220/32 , F05D2240/20 , F05D2240/55
摘要： A gas turbine engine rotor assembly is provided that includes a shaft, a rotor, and a seal assembly. The seal assembly is configured to seal between a first and second rotor compartments on opposite sides of the seal assembly. The seal assembly includes a seal groove and a split piston ring seal. The split piston ring seal is configured such that air in the first rotor compartment at P1 produces a radial force acting on the split piston ring seal, and air in the second rotor compartment at P2 produces a second force acting on the split piston ring seal, wherein the second force is directed radially inward and the first force is directed radially outward, and the second force is greater than the first force.
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公开(公告)号：US12116940B2
公开(公告)日：2024-10-15
申请号：US17215575
申请日：2021-03-29
CPC分类号： F02C9/20 , F02K3/04 , F04D27/0246 , F05D2270/023 , F05D2270/052 , F05D2270/053 , F05D2270/3011 , F05D2270/303 , F05D2270/304 , F05D2270/335 , F05D2270/71
摘要： Herein provided are methods and systems for controlling an engine having a variable geometry mechanism. A pressure ratio between a first pressure at an inlet of the engine and a predetermined reference pressure is determined. An output power for the engine is determined. The output power is adjusted based at least in part on the pressure ratio to obtain a corrected output power. A position control signal for a variable geometry mechanism of the engine is generated based on the corrected output power and the pressure ratio. The position control signal is output to a controller of the engine to control the variable geometry mechanism.
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公开(公告)号：US12116857B2
公开(公告)日：2024-10-15
申请号：US17920932
申请日：2021-04-22
发明人： Espen Soma , Tomas Solvig
IPC分类号： E21B33/068
CPC分类号： E21B33/068
摘要： An intervention apparatus for gaining lateral access to a well via a lateral access passage of the well is provided, including an outer pipe and a flexible guide pipe for guiding a flexible conduit towards the lateral access passage, the flexible guide pipe being arranged to be forwardly advanced in the outer pipe and to deform around a bend in the outer pipe as it is forwardly advanced.
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公开(公告)号：US12110116B1
公开(公告)日：2024-10-08
申请号：US18217228
申请日：2023-06-30
发明人： Ryan A. Mitchell , Robert B. Fowler
IPC分类号： B64D13/06 , B64D13/08 , B64D27/10 , F02C3/13 , F02C6/08 , F02C6/18 , F02C7/08 , F02C9/42 , F02K3/12
CPC分类号： B64D13/06 , B64D13/08 , B64D27/10 , F02C3/13 , F02C6/08 , F02C6/18 , F02C7/08 , F02C9/42 , F02K3/12
摘要： A method of operation is provided during which a heating fluid is directed through a first passage into a combustor section to heat a component within the combustor section when an aircraft engine is in a first standby mode. The aircraft engine includes a flowpath, a compressor section, the combustor section, a turbine section and an exhaust section. The flowpath extends through the compressor section, the combustor section, the turbine section and the exhaust section from an inlet into the flowpath to an exhaust from the flowpath. The heating fluid is directed through a second passage into the exhaust section when the aircraft engine is in a second mode. The heating fluid is directed through the second passage bypasses the turbine section.
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公开(公告)号：US12098647B2
公开(公告)日：2024-09-24
申请号：US17719037
申请日：2022-04-12
CPC分类号： F01D17/162 , F01D17/02 , G01B21/042 , F05D2270/802 , F05D2270/821
摘要： A method for calibrating a position sensor of a variable vane assembly for a gas turbine engine includes positioning an actuator member in at least one predetermined position, determining a first measured position of the actuator member in the at least one predetermined position with a first channel of a position sensor, determining a second measured position of the actuator member in the at least one predetermined position with a second channel of a position sensor, determining a measured position difference between the first measured position and the second measured position, and calibrating the second channel of the position sensor by adjusting the second measured position by the measured position difference to determine a second calibrated position.
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公开(公告)号：US12092040B2
公开(公告)日：2024-09-17
申请号：US18202727
申请日：2023-05-26
发明人： Paul R. Hanrahan
CPC分类号： F02C7/36 , B64C27/32 , B64D27/10 , B64D35/00 , F05D2260/40311 , F05D2260/90
摘要： An assembly is provided for an aircraft propulsion system. This assembly includes a sun gear, a ring gear, a plurality of intermediate gears, a carrier, a first brake and a second brake. The sun gear is rotatable about a centerline axis. The ring gear circumscribes the sun gear and is rotatable about the centerline axis. The intermediate gears are arranged circumferentially about the centerline axis. Each of the intermediate gears is meshed between the sun gear and the ring gear. The carrier is rotatable about the centerline axis. Each of the intermediate gears is rotatably mounted to the carrier. The first brake is configured to slow and/or stop rotation of the ring gear about the centerline axis. The second brake is configured to slow and/or stop rotation of the carrier about the centerline axis.
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公开(公告)号：US12092023B1
公开(公告)日：2024-09-17
申请号：US18121503
申请日：2023-03-14
CPC分类号： F02C3/305 , F02C3/30 , F02C7/18 , F23R3/10 , F23R2900/03044
摘要： An assembly is provided for a turbine engine. This assembly includes a housing, a combustor and a steam system. The housing includes an air plenum. The combustor is disposed within the air plenum. The combustor includes a combustion chamber and a combustor wall between the combustion chamber and the air plenum. The steam system includes a steam injector arranged within the air plenum next to the combustor wall. The steam system is configured to inject steam out of the steam injector and into the air plenum to impinge against the combustor wall.
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公开(公告)号：US12084733B1
公开(公告)日：2024-09-10
申请号：US18132687
申请日：2023-04-10
摘要： A mechanical surface treatment method for a workpiece includes using a multi-axis powered machine to actuate a deep rolling tool having a roller relative to the workpiece. The actuating includes applying the roller against a workpiece surface with a normal force sufficient to plastically deform the workpiece and translating the roller relative to the workpiece surface. The method includes concurrently applying an electrical current to the workpiece surface in a manner that produces an electroplastic effect at the workpiece surface and a near surface region. The electroplastic effect and the plastic deformation produce a refinement in a grain structure at the workpiece surface and near surface region and an increase in dislocation sources and tangles within the grain structure.
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