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公开(公告)号：US12158087B2
公开(公告)日：2024-12-03
申请号：US17744973
申请日：2022-05-16
Applicant: General Electric Company
Abstract: Fairing assemblies and methods for assembling gas turbine engine fairing assemblies are provided. For example, a fairing assembly comprises a plurality of fairings, an annular inner band defining a plurality of inner pockets, and an annular outer band defining a plurality of outer pockets. Each fairing has an inner end radially spaced apart from an outer end. Each inner pocket is shaped complementary to each fairing inner end and has forward and aft ends. Each outer pocket is shaped complementary to each fairing outer end and has forward and aft ends. The inner and outer bands are each a single piece structure. Each fairing inner end is received within one of the plurality of inner pockets, and each fairing outer end is received within one of the plurality of outer pockets. Some embodiments also comprise an inner ring positioned against the inner band to close the inner pockets.
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公开(公告)号：US20240229656A9
公开(公告)日：2024-07-11
申请号：US17970687
申请日：2022-10-21
Applicant: General Electric Company
Inventor： Abhijeet Jayshingrao Yadav , Nicholas Joseph Kray , Nicholas M. Daggett , Nitesh Jain , Matthew Mark Weaver , Srinivas Addagatla
IPC: F01D7/00
CPC classification number: F01D7/00 , F05D2220/323 , F05D2240/30
Abstract: A gas turbine engine includes a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order. A fan defining a fan axis and comprising a plurality of fan blades is rotatable about the fan axis. A pitch change mechanism is operable with the plurality of fan blades to control a pitch of the plurality of fan blades. A counterweight is connected to each respective fan blade. A spring mechanism is operably associated with each fan blade of the plurality of fan blades to create a spring twisting moment on the respective fan blade that is counter to a centrifugal twisting moment of the respective fan blade.
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公开(公告)号：US11655719B2
公开(公告)日：2023-05-23
申请号：US17232721
申请日：2021-04-16
Applicant: General Electric Company
Inventor： Matthew Mark Weaver , Dennis Paul Dry , Todd William Bachmann
CPC classification number: F01D5/26 , F01D5/10 , F01D5/3046 , F01D5/3084 , F05D2240/11 , F05D2300/6033
Abstract: An airfoil assembly for a turbine engine defines an axial direction, a radial direction, and a circumferential direction, and includes a first airfoil defining a first end along the radial direction, a first hub disposed on the first end of the first airfoil and having a first extension member extending at least partially in the radial direction, and a second airfoil adjacent to the first airfoil, the second airfoil defining a first end along the radial direction, a second hub disposed on the first end of the second airfoil and comprising a second extension member extending at least partially in the radial direction, and a circumferential bias assembly operable with the first extension member, the second extension member, or both for exerting a circumferential force on the first extension member, the second extension member, or both.
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公开(公告)号：US11262072B2
公开(公告)日：2022-03-01
申请号：US16902308
申请日：2020-06-16
Applicant: General Electric Company
Inventor： Brandon ALlanson Reynolds , Matthew Mark Weaver , Daniel Patrick Kerns
Abstract: Combustor dome assemblies having combustor deflectors are provided. For example, a combustor dome assembly comprises a combustor dome defining an opening; a ceramic matrix composite (CMC) deflector positioned adjacent the combustor dome on an aft side of the assembly; a fuel-air mixer defining a groove about an outer perimeter thereof; and a seal plate including a key. The CMC deflector includes a cup extending forward through the opening in the combustor dome that defines one or more bayonets and a slot. The bayonets are received in the fuel-air mixer groove, and the seal plate key is received in the CMC deflector slot. In another embodiment, where the seal plate may be omitted, a spring is positioned between the fuel-air mixer and the CMC deflector to hold the CMC deflector in place with respect to the combustor dome. Methods of assembling combustor dome assemblies having CMC deflectors also are provided.
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公开(公告)号：US20210254469A1
公开(公告)日：2021-08-19
申请号：US17170988
申请日：2021-02-09
Applicant: General Electric Company
Inventor： Darrell Glenn Senile , Matthew Mark Weaver , Alexander Martin Sener
Abstract: Airfoil assemblies for gas turbine engines are provided. For example, an airfoil assembly comprises an airfoil, an inner band defining an inner opening shaped complementary to an inner end of the airfoil, and an outer band defining an outer opening shaped complementary to an outer end of the airfoil. The airfoil inner end is received with the inner opening, and the airfoil outer end is received within the outer opening. A strut extends radially through an airfoil cavity. A first pad is defined at a first radial location within the cavity. A second pad is defined within the cavity at a second, different radial location. In some embodiments, the airfoil assembly inner band includes a first inner flange, through which the inner band is secured to a support structure, and the outer band includes a first outer flange, through which the outer band is secured to a support structure.
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Patent Agency Ranking
公开(公告)号：US20190003711A1
公开(公告)日：2019-01-03
申请号：US15421536
申请日：2017-02-01
Applicant: General Electric Company
Inventor： Brandon ALlanson Reynolds , Matthew Mark Weaver , Daniel Patrick Kerns
Abstract: Combustor dome assemblies having combustor deflectors are provided. For example, a combustor dome assembly comprises a combustor dome defining an opening; a ceramic matrix composite (CMC) deflector positioned adjacent the combustor dome on an aft side of the assembly; a fuel-air mixer defining a groove about an outer perimeter thereof; and a seal plate including a key. The CMC deflector includes a cup extending forward through the opening in the combustor dome that defines one or more bayonets and a slot. The bayonets are received in the fuel-air mixer groove, and the seal plate key is received in the CMC deflector slot. In another embodiment, where the seal plate may be omitted, a spring is positioned between the fuel-air mixer and the CMC deflector to hold the CMC deflector in place with respect to the combustor dome. Methods of assembling combustor dome assemblies having CMC deflectors also are provided.
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公开(公告)号：US20180163552A1
公开(公告)日：2018-06-14
申请号：US15372859
申请日：2016-12-08
Applicant: General Electric Company
Inventor： Brandon ALlanson Reynolds , Matthew Mark Weaver
CPC classification number: F01D9/065 , F01D5/282 , F01D5/284 , F01D9/02 , F01D9/042 , F02K3/04 , F05D2220/32 , F05D2240/122 , F05D2250/183 , F05D2260/202 , F05D2300/6033
Abstract: Turbine nozzle sections and airfoils having trailing edge segments are provided. In one embodiment, a turbine nozzle section comprises an inner band defining a pocket; an outer band defining an opening therethrough; and an airfoil radially extending from the inner band to the outer band and including pressure and suction sides. The airfoil has a body segment including a cavity and a plurality of ejector apertures defining a passageway from the cavity to an outer surface of the airfoil, and a trailing edge segment including an inner end and an outer end. The body segment defines a projection projecting inwardly from the suction side, and the trailing edge segment defines a notch opening toward the suction side. The projection is received within the notch. The inner end of the trailing edge segment is received within the inner band pocket, and the outer end is positioned within the outer band opening.
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公开(公告)号：US20240392965A1
公开(公告)日：2024-11-28
申请号：US18796453
申请日：2024-08-07
Applicant: General Electric Company
Inventor： Brandon ALlanson Reynolds , Matthew Mark Weaver , Daniel Patrick Kerns
Abstract: Combustor dome assemblies having combustor deflectors are provided. For example, a combustor dome assembly comprises a combustor dome defining an opening; a ceramic matrix composite (CMC) deflector positioned adjacent the combustor dome on an aft side of the assembly; a fuel-air mixer defining a groove about an outer perimeter thereof; and a seal plate including a key. The CMC deflector includes a cup extending forward through the opening in the combustor dome that defines one or more bayonets and a slot. The bayonets are received in the fuel-air mixer groove, and the seal plate key is received in the CMC deflector slot. In another embodiment, where the seal plate may be omitted, a spring is positioned between the fuel-air mixer and the CMC deflector to hold the CMC deflector in place with respect to the combustor dome. Methods of assembling combustor dome assemblies having CMC deflectors also are provided.
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9.发明申请公开(公告)号：US20220090504A1
公开(公告)日：2022-03-24
申请号：US17030595
申请日：2020-09-24
Applicant: General Electric Company
Inventor： Matthew Mark Weaver , Kirk Douglas Gallier
Abstract: A rotor blade for a gas turbine engine includes a structural member formed from a metallic material. The structural member, in turn, includes a base portion, a spar, and a tip cap, with the base portion at least partially forming a root of the rotor blade and a shank of the rotor blade. Furthermore, the structural member includes a fairing formed from a composite material. The fairing is, in turn, coupled to the structural member such that the fairing forms at least a portion of an airfoil of the rotor blade and a platform of the rotor blade. Additionally, the fairing including a first fairing panel and a second fairing panel in contact with the first fairing panel at a first split line and a second split line.
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公开(公告)号：US20200080425A1
公开(公告)日：2020-03-12
申请号：US16127483
申请日：2018-09-11
Applicant: General Electric Company
Inventor： Matthew Mark Weaver , Kurtis C. Montgomery , Michael James Verrilli
Abstract: A component for a gas turbine engine including a core and an outer enclosure. The core includes an exterior surface extending along a length between a first end and a second end and at least partially defines a cooling cavity on the exterior surface extending from the first end along at least a portion of the length. The cooling cavity is fluidly coupled to an air supply at the first end. The outer enclosure includes an outer surface. The outer enclosure is positioned outside the core and extends from the first end of the core along at least a portion of the length of the core and at least partially defines the cooling cavity.
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