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71.发明申请公开(公告)号：US20220251971A1
公开(公告)日：2022-08-11
申请号：US17170215
申请日：2021-02-08
Applicant: General Electric Company , General Electric Company Polska sp. z o.o. , General Electric Deutschland Holding GmbH
Inventor： Adam Tomasz Pazinski , Tomasz Jan Bulsiewcz , Bartlomiej Drozd , Miroslaw Czarnik , Mohamed Osama , John R. Yagielski
Abstract: A method of removing heat from an electrical machine located in a gas turbine engine at least partially inward of a core airflow path in a radial direction, the electrical machine comprising an outer electrical machine stator and an inner electrical machine rotor is provided. The method includes directing a liquid coolant radially inward past the outer electrical machine stator and toward an inner electrical machine rotor using a coolant passageway. The liquid coolant is directed onto and/or through one or both of the inner electrical machine rotor and a rotor support thereby removing heat from the inner electrical machine rotor.
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72.发明申请公开(公告)号：US20220251964A1
公开(公告)日：2022-08-11
申请号：US17170211
申请日：2021-02-08
Applicant: General Electric Company , General Electric Company Polska sp. z o.o. , General Electric Deutschland Holding GmbH
Inventor： Bartlomiej Drozd , Miroslaw Sobaniec , Mohamed Osama , Darek Zatorski
Abstract: A gas turbine engine includes an electrical machine positioned at least partially inward of a core airflow path, the electrical machine including an electrical rotor component and an electrical stator component, a connecting member positioned between the electrical machine and a rotary member, a disconnection device that is positionable between a disengaged position, in which the disconnection device is disengaged from the connecting member, and an engaged position, in which the disconnection device is engaged with the connecting member, and a controller including a processor, where the processor receives a signal from the electrical machine indicative of a fault, and in response to receiving the signal from the electrical machine indicative of the fault, directs the disconnection device to move from the disengaged position to the engaged position.
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公开(公告)号：US20220194617A1
公开(公告)日：2022-06-23
申请号：US17381448
申请日：2021-07-21
Applicant: General Electric Company Polska sp. z o.o.
Inventor： Tomasz Iglewski
Abstract: A screen for an air intake portion of a machine is provided. The screen includes an assembly of screen members that form a plurality of screen cells, wherein at least a portion of the screen cells define an irregular configuration.
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公开(公告)号：US11333041B2
公开(公告)日：2022-05-17
申请号：US17083565
申请日：2020-10-29
Applicant: General Electric Company Polska sp. z o.o.
Inventor： Michal Czarnecki , Michal Kowalczyk , Adam Krysztopa , Piotr Pachota
Abstract: An inner band assembly for at turbine nozzle of a rotary machine that includes a centerline axis, the inner band assembly comprising a platform portion, a first flange portion coupled to the platform portion and obliquely oriented with respect to the centerline axis, and a second flange coupled to the first flange and obliquely oriented with respect to the first flange. Wherein the platform portion and the first flange intersect.
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公开(公告)号：US20220055759A1
公开(公告)日：2022-02-24
申请号：US17381360
申请日：2021-07-21
Applicant: General Electric Company Polska sp. z o.o.
Inventor： Miroslaw Czarnik , Tomasz Edward Berdowski , Pawel Zdrojewski , Lukasz Maciej Janczak , Maciej Grunwald
Abstract: Propulsion engines and methods of accessing components within propulsor cavities of propulsion engines are disclosed. A propulsion engine includes an outer engine housing that includes a propulsor cavity located therein. The propulsor cavity is axially located between a low-pressure compressor and a fan of the propulsion engine. An electric converter is disposed within the propulsor cavity.
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Patent Agency Ranking
公开(公告)号：US20180370647A1
公开(公告)日：2018-12-27
申请号：US15986850
申请日：2018-05-23
Applicant: General Electric Company Polska SP z o.o.
Inventor： Tomasz IGLEWSKI
Abstract: An aircraft engine assembly can include an engine having an exhaust turbine with drive shaft and exhaust collector, a propeller rotationally coupled to the drive shaft and defining a rotational axis, and an exhaust stub to direct exhaust gases away from the aircraft.
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公开(公告)号：US20180363588A1
公开(公告)日：2018-12-20
申请号：US15992416
申请日：2018-05-30
Applicant: General Electric Company Polska Sp. Z o.o.
Inventor： Tomasz Iglewski
Abstract: An apparatus and method for an exhaust assembly for a turbine engine including a reverse flow portion. The exhaust assembly can include an exhaust stub extending between an exhaust collector and an exhaust outlet to define an exhaust conduit having the reverse flow portion. A flow of combustion gases can exit the engine and travel through the exhaust assembly. The exhaust assembly can be applied to a turboprop engine.
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公开(公告)号：US20250146426A1
公开(公告)日：2025-05-08
申请号：US19014361
申请日：2025-01-09
Inventor： Stefan Joseph Cafaro , Inenhe Mohammed Khalid , James Ryan Reepmeyer , Amit Zutshi , Daniel Edward Mollmann , Arjan Johannes Hegeman , Rafal Sarba
Abstract: A method of controlling an aeronautical gas turbine engine may be performed with an electronic controller. The method may include determining an airfoil pitch control command for at least one of a plurality of airfoils of the aeronautical gas turbine engine based at least in part on an excitation load acting upon the aeronautical gas turbine engine, and outputting the airfoil pitch control command to one or more actuators actuatable to change a pitch angle of the at least one of the plurality of airfoils. The airfoil pitch control command may be configured to augment and/or compensate for the excitation load acting upon the aeronautical gas turbine engine. The method may be embodied by a non-transitory computer-readable medium that includes computer-executable instructions, which when executed by a processor associated with the electronic controller, cause the electronic controller to perform the method.
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公开(公告)号：US12280883B2
公开(公告)日：2025-04-22
申请号：US18307917
申请日：2023-04-27
Inventor： William Joseph Bowden , Lukasz Ignacy Mazurkiewicz , Syed Arif Khalid , Trevor Howard Wood
Abstract: An aircraft defining a longitudinal centerline and extending between a forward end and an aft end is provided. The aircraft comprises a fuselage extending between the forward end of the aircraft and the aft end of the aircraft; a wing assembly extending laterally outwardly with respect to the longitudinal centerline from a portion of the fuselage; an unducted turbofan engine including an unducted fan that defines a plurality of fan wakes; and a pylon fairing that connects the unducted turbofan engine to the wing assembly, the pylon fairing defining a pylon fairing dihedral, wherein the pylon fairing dihedral is in a direction opposite the incoming fan flow swirl and associated sheared profiles of fan wakes upon arrival at the pylon leading edge.
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公开(公告)号：US12221894B2
公开(公告)日：2025-02-11
申请号：US18307450
申请日：2023-04-26
Applicant: General Electric Company Polska sp. z o.o.
Inventor： Dariusz Olczak
Abstract: A compressor comprises a rotor shaft including a forward end portion. The forward end portion defines an outer surface. A first row of compressor rotor blades is coupled to the rotor shaft downstream from the forward end portion. An outer casing at least partially surrounds the first row of compressor rotor blades and the outer surface of the forward end portion of the rotor shaft. The outer casing at least partially defines an inlet to the compressor. An inlet guide vane comprises a mounting portion, a tip portion, a leading-edge portion, and a trailing-edge portion. The mounting portion is coupled to the outer casing upstream from the first row of compressor rotor blades. The tip portion extends towards the outer surface of the forward end portion of the rotor shaft. A radial gap is defined between the tip portion and the outer surface.
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