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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：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：US20240191638A1
公开(公告)日：2024-06-13
申请号：US18581225
申请日：2024-02-19
发明人： Ashish Sharma , Tomasz Edward Berdowski , Maciej Czerwinski , Katarzyna Anna Mikolajczyk , Raymond Floyd Martell , Tomasz Jan Bulsiewicz
CPC分类号： F01D25/26 , F01D11/00 , F01D25/04 , F01D25/12 , F01D25/14 , B33Y80/00 , F05D2240/126 , F05D2240/14 , F05D2240/55 , F05D2250/182 , F05D2260/20 , F05D2260/96
摘要： Partition damper seal configurations for segmented internal cooling hardware apparatus are disclosed. An example airfoil includes an outer wall having a first rib spaced apart from a second rib on a surface of the outer wall, and an inner wall surrounded by the outer wall, the inner wall having a third rib protruding from the inner wall towards the surface of the outer wall, an end of the third rib detachably coupled to a portion of the surface of the outer wall, the portion of the surface positioned between the first rib and the second rib, the third rib and at least one of the first rib or the second rib to at least partially seal a flow passage between the inner and outer walls.
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公开(公告)号：US11905842B2
公开(公告)日：2024-02-20
申请号：US17553513
申请日：2021-12-16
发明人： Ashish Sharma , Tomasz Edward Berdowski , Maciej Czerwiński , Katarzyna Anna Mikolajczyk , Raymond Floyd Martell , Tomasz Jan Bulsiewicz
IPC分类号： F01D25/26 , F01D11/00 , F01D25/04 , F01D25/12 , F01D25/14 , B33Y80/00 , F01D5/16 , F01D5/26 , F01D9/04 , F01D5/14 , F01D9/06 , F01D25/24
CPC分类号： F01D25/26 , F01D11/00 , F01D25/04 , F01D25/12 , F01D25/14 , B33Y80/00 , F05D2240/126 , F05D2240/14 , F05D2240/55 , F05D2250/182 , F05D2260/20 , F05D2260/96
摘要： Partition damper seal configurations for segmented internal cooling hardware apparatus are disclosed. An example apparatus includes an inner wall and an outer wall, the outer wall spaced apart from the inner wall in a radial direction, a space between the inner and outer walls defining a flow passage, and a body positioned between the inner and outer walls, the body traversing the inner and outer walls in an axial direction and attached to an inner surface of the outer wall and an outer surface of the inner wall, the body to detach from the inner and outer surfaces and to at least partially seal the flow passage in response to the outer wall moving relative to the inner wall.
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公开(公告)号：US20230193784A1
公开(公告)日：2023-06-22
申请号：US17553513
申请日：2021-12-16
发明人： Ashish Sharma , Tomasz Edward Berdowski , Maciej Czerwinski , Katarzyna Anna Mikolajczyk , Raymond Floyd Martell , Tomasz Jan Bulsiewicz
摘要： Partition damper seal configurations for segmented internal cooling hardware apparatus are disclosed. An example apparatus includes an inner wall and an outer wall, the outer wall spaced apart from the inner wall in a radial direction, a space between the inner and outer walls defining a flow passage, and a body positioned between the inner and outer walls, the body traversing the inner and outer walls in an axial direction and attached to an inner surface of the outer wall and an outer surface of the inner wall, the body to detach from the inner and outer surfaces and to at least partially seal the flow passage in response to the outer wall moving relative to the inner wall.
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公开(公告)号：US11092084B2
公开(公告)日：2021-08-17
申请号：US15164946
申请日：2016-05-26
摘要： A gas turbine engine includes a combustion section, the combustion section including a plurality of fuel nozzles. A fuel delivery system for the gas turbine engine includes a feed tube and a fuel manifold fluidly connected to the feed tube for receiving fuel from the feed tube. The fuel delivery system also includes a pigtail fuel line fluidly connected to the fuel manifold and configured to fluidly connect to a fuel nozzle of the plurality of fuel nozzles when the fuel delivery system is installed in the gas turbine engine. In order to reduce an amount of hydraulic instability of a fuel flow through the fuel delivery system, at least one of the fuel manifold or the pigtail fuel line includes a means for damping a hydraulic instability within the fuel delivery system.
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公开(公告)号：US10711693B2
公开(公告)日：2020-07-14
申请号：US15647380
申请日：2017-07-12
摘要： A turbine engine has a core with a compressor, combustor, and turbine sections in axial flow arrangement and with corresponding rotating elements mounted to a shaft defining engine rotor elements. The turbine engine has a rotary driver operably coupled to the engine rotor elements. The turbine engine has at least one thermoelectric generator in thermal communication with the core and in electrical communication with the rotary driver to provide power to the rotary driver to turn the engine rotor elements.
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公开(公告)号：US20170342912A1
公开(公告)日：2017-11-30
申请号：US15164946
申请日：2016-05-26
CPC分类号： F02C9/26 , F02C7/222 , F02C7/228 , F05D2220/32 , F05D2240/35 , F05D2260/964 , F23R3/28 , F23R3/346 , Y02T50/672
摘要： A gas turbine engine includes a combustion section, the combustion section including a plurality of fuel nozzles. A fuel delivery system for the gas turbine engine includes a feed tube and a fuel manifold fluidly connected to the feed tube for receiving fuel from the feed tube. The fuel delivery system also includes a pigtail fuel line fluidly connected to the fuel manifold and configured to fluidly connect to a fuel nozzle of the plurality of fuel nozzles when the fuel delivery system is installed in the gas turbine engine. In order to reduce an amount of hydraulic instability of a fuel flow through the fuel delivery system, at least one of the fuel manifold or the pigtail fuel line includes a means for damping a hydraulic instability within the fuel delivery system.
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公开(公告)号：US09784187B2
公开(公告)日：2017-10-10
申请号：US14407400
申请日：2013-06-14
发明人： Jared Matthew Wolfe , Joshua Daniel Brown , Christopher Francis Poranski , Edward J. Condrac , Raymond Floyd Martell
摘要： A gas turbine engine is provided. The gas turbine engine includes a compressor assembly and a combustion assembly in flow communication with the compressor assembly. The combustion assembly includes a plurality of fuel nozzles and a fluid conduit for delivering fuel to the fuel nozzles. The fluid conduit has a plurality of first outlet ports that are spaced apart from one another along the fluid conduit, and the fluid conduit also has a plurality of second outlet ports that are spaced apart from one another along the fluid conduit. The fluid conduit further has a first flow path extending along the fluid conduit in flow communication with the first outlet ports, and the fluid conduit also has a second flow path extending along the fluid conduit in flow communication with the second outlet ports. At least a portion of the first flow path is circumscribed by the second flow path.
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公开(公告)号：US11662150B2
公开(公告)日：2023-05-30
申请号：US16992474
申请日：2020-08-13
CPC分类号： F28D7/0016 , F28F9/0243 , F28F2009/029 , F28F2009/0287 , F28F2210/10
摘要： A heat exchanger for a gas turbine engine includes a heat exchanger body having a first surface and a second surface oriented at least partially at an oblique angle relative to the first surface. The heat exchanger body defines a plenum extending between the first and second surfaces. Furthermore, the heat exchanger body defines a fluid passage extending through the second surface such that the fluid passage is in fluid communication with the plenum. The fluid passage, in turn, includes first and second portions. The first portion intersects the plenum at an intersection and defines a line of projection extending normal to the second surface. The second portion defines a line of projection extending normal to the first surface. The fluid passage further includes a curved portion extending from the first portion to the second portion.
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