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11.发明申请公开(公告)号：US20220255396A1
公开(公告)日：2022-08-11
申请号：US17170216
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 , Mohamed Osama , Christopher Delametter
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 including an outer generator stator and an inner generator rotor is provided. The method includes directing cooling airflow radially through an airflow passageway to an enclosure at least partially defined by a thermal shield at least partially around the electrical machine. The cooling airflow is directed radially inward past the outer generator stator and toward the inner generator rotor using a cooling manifold thereby removing heat from the generator rotor.
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公开(公告)号：US20220251965A1
公开(公告)日：2022-08-11
申请号：US17170229
申请日：2021-02-08
Applicant: General Electric Company , General Electric Company Polska sp. z o.o. , General Electric Deutschland Holding GmbH
Inventor： Miroslaw Czarnik , Adam Tomasz Pazinski , Bartlomiej Drozd , Darek Zatorski , Maciej Krzysztof Grunwald , Mohamed Osama , John R. Yagielski
Abstract: An electrical machine includes a stator assembly coupled to an engine stator component of a propulsion engine. The stator assembly includes a stator support assembly fixedly attached to the engine stator component and a stator disposed on the stator support structure. An electrical machine shaft is coupled to an end of a shaft of the propulsion engine via an intermediate shaft member extending axially between the end of the shaft and the electrical machine shaft. A bearing support frame extends from the propulsion engine, the bearing support frame defining a bearing cavity in conjunction with the electrical machine shaft. Electrical machine bearings radially extend from the bearing support frame to rotatably contact the electrical machine shaft. A rotor attached to a rotor support structure attached to the electrical machine shaft. The rotor rotates in conjunction with the electrical machine shaft to exchange energy with the shaft of the propulsion engine.
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公开(公告)号：US20190048798A1
公开(公告)日：2019-02-14
申请号：US16028589
申请日：2018-07-06
Inventor： Estera SLAWINSKA , Krzysztof KORZEPSKI , John Alan MANTEIGA , Artur KOLODZIEJCZYK
Abstract: An inlet frame and a method of additively manufacturing the same are provided. The inlet frame includes a forward annular body spaced apart from a rear annular body to define an inlet passageway in fluid communication with a compressor inlet. The inlet frame may define integral wash manifolds and discharge ports for directing a flow of wash fluid directly through the compressor inlet. In addition, inlet frame may define one or more integral annular heating plenums in fluid communication with a hot air source for heating regions of the inlet frame that are prone to icing conditions.
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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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Patent Agency Ranking
公开(公告)号：US20250043719A1
公开(公告)日：2025-02-06
申请号：US18926865
申请日：2024-10-25
Inventor： Arthur William Sibbach , Adam Tomasz Pazinski
Abstract: An aircraft engine assembly includes a gas turbine engine having an intake channel configured to receive an incoming flow of air and thereby form an intake flow of air, the intake channel configured to turn the received incoming flow of air from an incoming flow direction to a first axial direction of the gas turbine engine, the incoming flow direction reverse of the first axial direction, and an electric machine coupled with the low pressure shaft and located at the aft end of the gas turbine engine proximate the intake channel, the electric machine in heat exchange communication with the intake flow of air such that the electric machine transfers heat to the incoming flow of air within the intake channel when the electric machine is operated.
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公开(公告)号：US20240318573A1
公开(公告)日：2024-09-26
申请号：US18357282
申请日：2023-07-24
Inventor： Sajinu Nangariyil , Ravindra Shankar Ganiger , Abhilash Pillai , Adam Tomasz Pazinski , David Raju Yamarthi
IPC: F01D11/08
CPC classification number: F01D11/08 , F05D2220/323 , F05D2240/55
Abstract: A turbine engine is provided. The gas turbine engine defines a radial direction and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly comprising a seal segment, the seal segment having a seal face configured to form a fluid bearing with the rotor; and a seal support assembly, the seal support assembly including a magnet assembly having a magnet coupled to the carrier or the seal segment for biasing the first seal segment along the radial direction.
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公开(公告)号：US20240052753A1
公开(公告)日：2024-02-15
申请号：US18081862
申请日：2022-12-15
Inventor： Amit Zutshi , Rafal Sarba , James Ryan Reepmeyer , Stefan Joseph Cafaro , Inenhe Mohammed Khalid , Daniel Edward Mollmann , Arjan Johannes Hegeman
Abstract: An open rotor engine includes a core engine, a plurality of guide vanes positioned within or extending from the core engine; and a pitch change assembly operably coupled to the plurality of guide vanes. The pitch change assembly includes one or more actuators configured to change a pitch angle of respective ones of the plurality of guide vanes, and a plurality of linkage arms that are respectively movable by actuation of at least one of the one or more actuators. The plurality of linkage arms are directly or indirectly coupled to a corresponding one of the plurality of guide vanes. The plurality of linkage arms may have a length that differs from one another, and such length may orient a displacement or a range of motion of the respective linkage arm to an envelope of rotation about a guide vane axis that differs as between the plurality of guide vanes.
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公开(公告)号：US20230378827A1
公开(公告)日：2023-11-23
申请号：US18085962
申请日：2022-12-21
Applicant: General Electric Company , General Electric Deutschland Holding GmbH , General Electric Company Polska Sp. z o.o.
Inventor： Bugra Han Ertas , Joseph John Zierer, JR. , Vandana Prabhakar Rallabandi , David Allan Torrey , David William Crall , Mohamed Osama , Adam Tomasz Pazinski , Arthur William Sibbach
CPC classification number: H02K1/20 , H02K5/203 , H02K7/1823 , H02K21/14 , F02C6/00
Abstract: An airgap cooling system (140) for an electric machine (100), the electric machine (100) including a rotor assembly (102) rotatably mounted within a stator assembly (120) and defining an airgap (130) therebetween, wherein the stator assembly (120) comprises a lamination stack (124). The airgap cooling system (140) includes a plurality of distribution passages (142) that extend through the lamination stack (124); a plurality of discharge passages (150) that extend between the plurality of distribution passages (142) and the airgap (130); a cooling manifold (160) defining an annular distribution plenum (164) in fluid communication with the plurality of distribution passages (142), wherein the cooling manifold (160) is configured for receiving a cooling fluid (144) and directing the cooling fluid (144) into the distribution plenum (164), through the distribution passage (142) and the discharge passage (150), and into the airgap (130).
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公开(公告)号：US11735982B2
公开(公告)日：2023-08-22
申请号：US17205028
申请日：2021-03-18
Applicant: General Electric Company , General Electric Company Polska Sp. z o.o. , General Electric Deutschland Holding GmbH
Inventor： Mohamed Osama , Bartlomiej Drozd , John Russell Yagielski
CPC classification number: H02K11/40 , F02C6/206 , H02K7/1823 , H02K11/02 , H02K11/21 , H02K24/00 , H03H1/0007 , F05D2220/323 , F05D2220/76
Abstract: A hybrid-electric propulsion system is provided. In one example aspect, the hybrid-electric propulsion system includes a power converter and a propulsor. The propulsor includes a gas turbine engine having a shaft and one or more bearings supporting the shaft. The propulsor also includes an electric machine electrically coupled with the power converter. The electric machine includes a stator assembly and a rotor assembly. The rotor assembly has a rotor and a rotor connection assembly. The rotor connection assembly operatively couples the rotor with the shaft. The rotor connection assembly has an insulated joint for interrupting common mode electric current from flowing from the rotor of the electric machine to the shaft. A grounding device is included to electrically ground the shaft. The power converter includes an electromagnetic interference filter to reduce common mode voltage reaching the electric machine.
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