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公开(公告)号：US20230366326A1
公开(公告)日：2023-11-16
申请号：US17980365
申请日：2022-11-03
发明人： Jakub Kulecki
CPC分类号： F01D25/02 , H05B1/023 , H05B3/18 , H02K21/28 , H05B2214/02
摘要： Methods, apparatus, systems, and articles of manufacture are disclosed to heat rotor blades. An example blade heating apparatus includes a stationary magnet; a solenoid to rotate around or inside the stationary magnet, the rotation to generate electricity using the solenoid; and a heating element embedded in a rotor blade, the heating element to increase a temperature of the rotor blade using the electricity to mitigate icing.
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公开(公告)号：US20230344322A1
公开(公告)日：2023-10-26
申请号：US18338390
申请日：2023-06-21
申请人： General Electric Company , General Electric Deutschland Holding GmbH , General Electric Company Polska Sp. z o.o.
CPC分类号： H02K11/40 , H02K11/21 , F02C6/206 , H02K7/1823 , H02K11/02 , H02K24/00 , H03H1/0007 , F05D2220/323 , F05D2220/76
摘要： A propulsor is provided including a gas turbine engine having a shaft and one or more bearings supporting the shaft, a rotor hub operatively coupled to the shaft and comprising a hub flange, an electric machine comprising a stator assembly and a rotor assembly, a rotor connection member operatively coupled to the rotor assembly of the electric machine and comprising a connection flange, and an insulated joint for operatively coupling the rotor assembly with the shaft. The insulated joint includes a plurality of insulative layers, at least one of the plurality of insulative layers extending between the hub flange and the connection flange to interrupt common mode electric current from flowing between the rotor assembly and the shaft.
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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
发明人： Elzbieta Kryj-Kos , Piotr Jerzy Kulinski , Pawel Adam Lewicki , Ruolong Ma , Wendy Wenling Lin , Patrick Keene Clements
IPC分类号： F01D9/02
CPC分类号： F01D9/02 , F05D2230/31 , F05D2240/121 , F05D2250/185
摘要： 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分类号： F01D5/141 , F01D25/28 , F05D2260/961
摘要： 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
申请人： General Electric Company , General Electric Deutschland Holding GmbH , General Electric Company Polska Sp. z o.o.
发明人： Tomasz Edward Berdowski , Ashish Sharma , Raymond Floyd Martell , Piotr Jerzy Kulinski , Lukasz Maciej Janczak
CPC分类号： F01D11/18 , F01D25/26 , F05D2240/11 , F05D2260/38
摘要： 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
申请人： GE Avio S.r.l. , General Electric Company Polska sp. z o.o , General Electric Deutschland Holding GmbH
IPC分类号： F23M20/00
CPC分类号： F23M20/005 , F05B2260/96 , F23R2900/00013 , F23R2900/00014
摘要： 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
申请人： General Electric Company , General Electric Deutschland Holding GmbH , General Electric Company Polska Sp. z o.o.
发明人： Ashish Sharma , Piotr Jerzy Kulinski , Adam Tomasz Pazinski , Tomasz Jan Bulsiewicz , Scott Alan Schimmels
IPC分类号： F01D11/24
CPC分类号： F01D11/24 , F05D2220/32 , F05D2240/55 , F05D2260/213
摘要： 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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公开(公告)号：US11499479B2
公开(公告)日：2022-11-15
申请号：US16057892
申请日：2018-08-08
发明人： 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
摘要： 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
申请人： General Electric Company , General Electric Company Polska Sp. z o.o. , General Electric Deutschland Holding GmbH
摘要： 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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50.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
申请人： General Electric Company , General Electric Company Polska sp. z o.o. , General Electric Deutschland Holding GmbH
发明人： Adam Tomasz Pazinski , Tomasz Jan Bulsiewcz , Bartlomiej Drozd , Miroslaw Czarnik , Mohamed Osama , John R. Yagielski
摘要： 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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