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公开(公告)号：US11725524B2
公开(公告)日：2023-08-15
申请号：US17389945
申请日：2021-07-30
Inventor： Elzbieta Kryj-Kos , Piotr Jerzy Kulinski , Pawel Adam Lewicki , Ruolong Ma , Wendy Wenling Lin , Patrick Keene Clements
IPC: F01D9/02
CPC classification number: F01D9/02 , F05D2230/31 , F05D2240/121 , F05D2250/185
Abstract: An airfoil for a gas turbine engine defining a spanwise direction, a root end, a tip end, a leading edge end, and trailing edge end is provided. The airfoil includes: a body extending along the spanwise direction between the root end and the tip end, the body formed of a composite material; and a sculpted leading edge member attached to the body positioned at the leading edge end of the airfoil, the sculped leading edge member formed at least in part of a metal material and defining a non-linear patterned leading edge of the airfoil.
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公开(公告)号：US20230250723A1
公开(公告)日：2023-08-10
申请号：US17839859
申请日：2022-06-14
CPC classification number: F01D5/141 , F01D25/28 , F05D2260/961
Abstract: An airfoil assembly for a gas turbine engine includes: an inner support structure configured to circumscribe a longitudinal axis of the gas turbine engine; an outer support structure configured to circumscribe the longitudinal axis of the gas turbine engine, the outer support structure circumscribing the inner support structure; and a stage including a plurality of airfoils extending from the inner support structure towards the outer support structure, the plurality of airfoils including: a first airfoil defining a first sweep angle, a first axial position, and a first lean angle; and a second airfoil defining a second sweep angle, a second axial position, and a second lean angle, wherein the second sweep angle is different than the first sweep angle, the second axial position is different than the first axial position, the second lean angle is different than the first lean angle, or a combination thereof.
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公开(公告)号：US11719115B2
公开(公告)日：2023-08-08
申请号：US17561182
申请日：2021-12-23
Applicant: General Electric Company , General Electric Deutschland Holding GmbH , General Electric Company Polska Sp. z o.o.
Inventor： Tomasz Edward Berdowski , Ashish Sharma , Raymond Floyd Martell , Piotr Jerzy Kulinski , Lukasz Maciej Janczak
CPC classification number: F01D11/18 , F01D25/26 , F05D2240/11 , F05D2260/38
Abstract: A gas turbine engine including a first turbine rotor assembly having a plurality of first turbine rotor blades extended within a gas flowpath, and a second turbine rotor assembly positioned aft along the gas flowpath of the first turbine rotor assembly. The second turbine rotor assembly is rotatably separate from the first turbine rotor assembly. A casing surrounds the first turbine rotor assembly. The casing has a unitary, integral outer casing wall extended forward of the first turbine rotor assembly and aft of the first turbine rotor assembly. The casing includes a plurality of vanes extended from the outer casing wall and through the gas flowpath aft of the first turbine rotor assembly and forward of the second turbine rotor assembly. The casing includes a plurality of walls forming thermal control rings extended outward along the radial direction from the outer casing wall. The outer casing wall and the thermal control rings is a unitary, integral structure.
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公开(公告)号：US20230175692A1
公开(公告)日：2023-06-08
申请号：US17806116
申请日：2022-06-09
Applicant: GE Avio S.r.l. , General Electric Company Polska sp. z o.o , General Electric Deutschland Holding GmbH
Inventor： Krzysztof Kostrzewa , Roberto Ferraro , Krzysztof Benkiewicz
IPC: F23M20/00
CPC classification number: F23M20/005 , F05B2260/96 , F23R2900/00013 , F23R2900/00014
Abstract: A combustor includes an annular dome and a plurality of dampers integral with the annular dome. Each of the plurality of dampers includes an adjustable damper cover and a damper portion defining a cavity having a volume. The damper cover is mounted to the damper portion integrated with the annular dome and is movable to adjust the volume of the cavity to adjust a frequency of each of the plurality of dampers to reduce an acoustic amplitude of the combustor.
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公开(公告)号：US20230143283A1
公开(公告)日：2023-05-11
申请号：US17561203
申请日：2021-12-23
Applicant: General Electric Company , General Electric Deutschland Holding GmbH , General Electric Company Polska Sp. z o.o.
Inventor： Ashish Sharma , Piotr Jerzy Kulinski , Adam Tomasz Pazinski , Tomasz Jan Bulsiewicz , Scott Alan Schimmels
IPC: F01D11/24
CPC classification number: F01D11/24 , F05D2220/32 , F05D2240/55 , F05D2260/213
Abstract: A method of operating a gas turbine engine comprising: extracting a flow of air from a compressor section of the gas turbine engine into a first conduit; flowing the extracted flow of air through the first conduit to a first location at a turbine section of the turbine section, wherein a second conduit is in fluid communication with the turbine section at a second location; flowing a heat transfer fluid to a first heat exchanger positioned in thermal communication with the flow of air through the first conduit, the heat transfer fluid in thermal communication with the extracted flow of air through the first conduit via the first heat exchanger; and modulating, via a flow control device, a portion of the flow of air extracted from the first conduit to the second conduit downstream of the first heat exchanger.
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Patent Agency Ranking
公开(公告)号：US11499479B2
公开(公告)日：2022-11-15
申请号：US16057892
申请日：2018-08-08
Inventor： Kenneth Arthur Gould , Abdus Shamim , Jaroslaw Henryk Dekowski , Piotr Sebastian Hance , Przemyslaw Slawomir Tkaczyk , Marcin Pawel Faber , Adam Krysztopa , Piotr Lech Bar , Krzysztof Chelstowski , Craig Alan Gonyou , Robert John Parks
Abstract: A gas turbine engine having an improved air delivery system that includes features for pressurizing and/or cooling various components of the engine while minimizing the impact to the cycle efficiency of the engine, reducing the weight of the engine, and reducing the specific fuel consumption of the engine is provided.
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公开(公告)号：US20220302801A1
公开(公告)日：2022-09-22
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
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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68.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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69.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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