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公开(公告)号：US20250146442A1
公开(公告)日：2025-05-08
申请号：US18802001
申请日：2024-08-13
Applicant: GE Avio S.r.l.
Inventor： Vincenzo Martina , Lucia Azzini , Daniele Coutandin
Abstract: An aircraft system is provided. The aircraft system includes: a gas turbine engine; a fuel system having a fuel tank and a fuel delivery system fluidly connecting the fuel tank to the gas turbine engine; an electric drive assembly including a component module; and a thermal management system including: a thermal fluid loop; a heat source heat exchanger in thermal communication with the component module and the thermal fluid loop; an airflow heat sink heat exchanger in thermal communication with the thermal fluid loop and further configured to be in thermal communication with a cooling airflow during operation of the gas turbine engine; and a fuel heat sink heat exchanger in selective thermal communication with the thermal fluid loop, the fuel tank, or both, the fuel heat sink heat exchanger in fluid communication with the fuel tank independently of the fuel delivery system during at least a first operating condition.
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公开(公告)号：US20250101919A1
公开(公告)日：2025-03-27
申请号：US18976748
申请日：2024-12-11
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Daniel Alan Niergarth , Jorge de Luis , Douglas Downey Turner , Michael Macrorie , Keith W. Wilkinson , Arthur William Sibbach , Vincenzo Martina
Abstract: A gas turbine engine is provided having a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches and the turbine section having a drive turbine defining a drive turbine exit area (ADTExit) in square inches, the turbomachine further comprising a drive turbine shaft coupled to the drive turbine; wherein the gas turbine engine defines a maximum exhaust gas temperature (EGT) in degrees Celsius, a maximum drive turbine shaft torque (TOUT) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein the corrected specific power is determined as follows: ( T OUT A DTExit ) 2 * EGT A HPCExit * 1 0 - 1 1 ; wherein CSP is greater than 0.0001194×EGT2−0.103×EGT+22.14 and less than 0.0003294×EGT2−0.306×EGT+77.91; and wherein EGT is greater than 525 degrees Celsius and less than 1250 degrees Celsius.
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公开(公告)号：US20250101916A1
公开(公告)日：2025-03-27
申请号：US18972172
申请日：2024-12-06
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Bugra H. Ertas , Xiaohua Zhang , Miriam Manzoni , Flavia Turi , Andrea Piazza , Arthur W. Sibbach , Brandon W. Miller
Abstract: A gas turbine engine includes a gearbox assembly that includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio defined by: V G V G B · V G is a gutter volume of the gutter and VGB is a gearbox volume. The gas turbine engine includes a lubricant flow control system that includes a variable flow lubricant pump that generates a pump variable flow of lubricant to the gearbox assembly. The gearbox assembly has a variable consumption demand for delivery of lubricant. A lubricant flow controller is configured to generate a pump control command for the variable flow lubricant pump to produce the pump variable flow of lubricant based on the variable consumption demand.
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公开(公告)号：US20250101911A1
公开(公告)日：2025-03-27
申请号：US18972209
申请日：2024-12-06
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Bugra H. Ertas , Xiaohua Zhang , Miriam Manzoni , Flavia Turi , Andrea Piazza , Arthur W. Sibbach
Abstract: A gas turbine engine includes a fan, a combustor positioned in a core air flowpath that generates combustion gases, a steam system that extracts water from the combustion gases and generates steam, and a gearbox assembly. The steam system includes water storage devices that store the water therein. The water storage devices include a first state in which a level of the water increases or is maintained and a second state in which the level of the water decreases as the water flows through the water storage devices. The gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio defined by: V G V G B · V G is a gutter volume of the gutter and VGB is a gearbox volume.
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公开(公告)号：US12258878B2
公开(公告)日：2025-03-25
申请号：US18320564
申请日：2023-05-19
Applicant: GE Avio S.r.l.
Inventor： Pietro Molesini , Alberto Frezet , Saypen Baraggia Au Yeung
Abstract: A lubricant system for supplying lubrication to a component in a turbine engine includes a lubricant reservoir, a supply line fluidly coupling the lubricant reservoir to the component in the turbine engine, a scavenge line fluidly coupling the component to the lubricant reservoir, and a bypass line fluidly coupling the supply line to the scavenge line and bypassing the component.
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Patent Agency Ranking
公开(公告)号：US20250035052A1
公开(公告)日：2025-01-30
申请号：US18913330
申请日：2024-10-11
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Bugra H. Ertas , Ravindra Shankar Ganiger , Andrea Piazza , Brandon W. Miller
IPC: F02C7/36
Abstract: A mounting assembly for a gearbox assembly of a gas turbine engine includes at least one mounting member configured to mount a gear of the gearbox assembly to a component of the gas turbine engine, the at least one mounting member characterized by a lateral impedance parameter, a bending impedance parameter, and a torsional impedance parameter. A gas turbine engine includes the mounting assembly. The at least one mounting member may be a flex mount, a fan frame, or a flex coupling. The gas turbine engine also includes a heat exchanger including an inner peripheral wall and an outer peripheral wall extending between an inlet and an outlet. The inner peripheral wall and the outer peripheral wall define a flow channel therebetween. The heat exchanger includes a plurality of fins disposed in the flow channel and dividing the flow channel into a plurality of flow passages.
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公开(公告)号：US20250026470A1
公开(公告)日：2025-01-23
申请号：US18439870
申请日：2024-02-13
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Mehdi Milani Baladi , Randy M. Vondrell
Abstract: A hybrid electric aircraft equipped with gyroscopic stabilization control is provided. In one aspect, a hybrid electric aircraft includes a turbo-generator having a gas turbine engine and an electric generator operatively coupled thereto for generating electrical power. The turbo-generator defines a rotation axis. The aircraft also includes one or more electrically-driven propulsors for producing thrust for the aircraft. In addition, the aircraft includes a pivot mount operatively coupled with the turbo-generator. To provide gyroscopic stabilization control of the aircraft, the pivot mount is controlled to adjust the rotation axis of the turbo-generator relative to a prime stability axis of the aircraft. Additionally or alternatively, a rotational speed of the turbo-generator can be changed to provide gyroscopic stabilization control of the aircraft.
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公开(公告)号：US12203418B2
公开(公告)日：2025-01-21
申请号：US17929105
申请日：2022-09-01
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Bugra H. Ertas , Ravindra Shankar Ganiger , Andrea Piazza
IPC: F02C7/36 , F16H57/025 , F16H57/08
Abstract: A mounting assembly for a gearbox assembly of a gas turbine engine includes at least one mounting member configured to mount a gear of the gearbox assembly to a component of the gas turbine engine, the at least one mounting member characterized by a lateral impedance parameter, a bending impedance parameter, and a torsional impedance parameter. A gas turbine engine includes the mounting assembly. The at least one mounting member may be a flex mount, a fan frame, or a flex coupling.
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公开(公告)号：US20250003482A1
公开(公告)日：2025-01-02
申请号：US18510014
申请日：2023-11-15
Applicant: GE Avio S.r.l.
Inventor： Miriam Manzoni , Michele Gravina , Federico Leonardi , Alessandro Anderlini
IPC: F16H57/04
Abstract: A lubrication system for a gear assembly. The gear assembly includes a first gear and a second gear. The first gear and the second gear mesh with each other at a mesh. The lubrication system includes one or more lubricant injectors. The one or more lubricant injectors include one or more first lubricant outlets directed to the mesh. The one or more first lubricant outlets supply a first portion of lubricant to the mesh. The one or more lubricant injectors include one or more second lubricant outlets directed to a location that is different than the mesh. The one or more second lubricant outlets supply a second portion of lubricant to the location different than the mesh.
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公开(公告)号：US12168239B2
公开(公告)日：2024-12-17
申请号：US17643544
申请日：2021-12-09
Applicant: GE Avio S.r.l.
Inventor： Saypen Baraggia Au Yeung , Pietro Molesini , Miriam Manzoni , Fabio De Bellis
Abstract: An air/oil separator is provided. The air/oil separator includes an oil manifold having a first air/oil inlet and a second air/oil inlet; a first separation chamber in communication with the first air/oil inlet; and a second separation chamber separate from the first separation chamber, the second separation chamber in communication with the second air/oil inlet.
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