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公开(公告)号：US12123324B2
公开(公告)日：2024-10-22
申请号：US18343013
申请日：2023-06-28
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： A method of electroforming an airfoil comprising an airfoil body. The method comprising electroforming a metal edge shell over a filler, located at a leading edge of the airfoil body, and over the airfoil body. The filler can be encapsulated within the metal edge shell and the metal edge shell has a sculpted leading edge defining a non-linear pattern.
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公开(公告)号：US11788425B2
公开(公告)日：2023-10-17
申请号：US17561156
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
CPC分类号： F01D11/18 , F01D9/04 , F01D11/24 , F01D25/24 , F01D25/246 , F05D2220/32 , F05D2260/201
摘要： A gas turbine engine including: a first turbine rotor assembly including a plurality of first turbine rotor blades extended within a gas flowpath; and a casing surrounding the first turbine rotor assembly, wherein the casing comprises an outer casing wall extended around the first turbine rotor assembly; a plurality of vanes extended from the outer casing wall and within the gas flowpath at a location aft of the first turbine rotor assembly; and a thermal control ring positioned outward along a radial direction from the outer casing wall, and wherein the thermal control ring comprises a body and a plurality of pins, and wherein the plurality of pins extend between the outer casing wall and the body.
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公开(公告)号：US11859500B2
公开(公告)日：2024-01-02
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：US20230407758A1
公开(公告)日：2023-12-21
申请号：US18452764
申请日：2023-08-21
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：US20230146084A1
公开(公告)日：2023-05-11
申请号：US17561156
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
CPC分类号： F01D11/18 , F01D9/04 , F01D25/24 , F05D2220/32
摘要： A gas turbine engine including: a first turbine rotor assembly including a plurality of first turbine rotor blades extended within a gas flowpath; and a casing surrounding the first turbine rotor assembly, wherein the casing comprises an outer casing wall extended around the first turbine rotor assembly; a plurality of vanes extended from the outer casing wall and within the gas flowpath at a location aft of the first turbine rotor assembly; and a thermal control ring positioned outward along a radial direction from the outer casing wall, and wherein the thermal control ring comprises a body and a plurality of pins, and wherein the plurality of pins extend between the outer casing wall and the body.
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公开(公告)号：US20230340885A1
公开(公告)日：2023-10-26
申请号：US18343013
申请日：2023-06-28
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： A method of electroforming an airfoil comprising an airfoil body. The method comprising electroforming a metal edge shell over a filler, located at a leading edge of the airfoil body, and over the airfoil body. The filler can be encapsulated within the metal edge shell and the metal edge shell has a sculpted leading edge defining a non-linear pattern.
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公开(公告)号：US20230147089A1
公开(公告)日：2023-05-11
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：US20220307380A1
公开(公告)日：2022-09-29
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
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：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：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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