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公开(公告)号：US20230399955A1
公开(公告)日：2023-12-14
申请号：US18354774
申请日：2023-07-19
Applicant: General Electric Company
Inventor： Jonathan Michael Rausch , Zachary Daniel Webster , Kevin Robert Feldmann , Andrew David Perry , Kirk Douglas Gallier , Daniel Endecott Osgood
IPC: F01D5/18
CPC classification number: F01D5/187 , F05D2260/202 , F05D2240/30
Abstract: A turbine engine includes an engine core extending along an engine centerline and includes a compressor section, a combustor, and a turbine section in serial flow arrangement. One or more blades in the compressor or turbine sections has an internal cooling conduit with at least one of a bend or a terminal end. A plurality of cooling holes are provided in the blade, with each hole having an inlet fluidly coupled to the cooling conduit and an outlet opening onto an exterior of the blade.
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公开(公告)号：US11591965B2
公开(公告)日：2023-02-28
申请号：US17215130
申请日：2021-03-29
Applicant: General Electric Company
Inventor： Christopher Edward Wolfe , Hendrik Pieter Jacobus de Bock , William Dwight Gerstler , Brian Gene Brzek , Brandon Wayne Miller , Daniel Alan Niergarth , Kevin Robert Feldmann , Kevin Edward Hinderliter
Abstract: A thermal management system for transferring heat between fluids includes a thermal transport bus through which a heat exchange fluid flows. Additionally, the system includes a heat source heat exchanger arranged along the bus such that heat is added to the fluid flowing through the heat source heat exchanger. Moreover, the system includes a plurality of heat sink heat exchangers arranged along the bus such that heat is removed from the fluid flowing through the plurality of heat sink heat exchangers. Furthermore, the system includes a bypass conduit fluidly coupled to the bus such that the bypass conduit allows the fluid to bypass one of the heat source heat exchanger or one of the heat sink heat exchangers. In addition, the system includes a valve configured to control a flow of the fluid through the bypass conduit based on a pressure of the fluid within the bus.
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公开(公告)号：US11280215B2
公开(公告)日：2022-03-22
申请号：US15522854
申请日：2015-10-28
Applicant: General Electric Company
Inventor： Robert Frederick Bergholz , Jason Randolph Allen , Robert David Briggs , Kevin Robert Feldmann , Curtis Walton Stover , Zachary Daniel Webster , Fernando Reiter
IPC: F01D25/12 , F23R3/00 , F01D5/18 , F23R3/06 , F01D9/04 , F01D11/08 , F02C3/04 , F02C7/18 , F23R3/04
Abstract: An engine component assembly includes a first engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface with at least one cavity. A second engine component is spaced from the cooling surface, and includes at least one cooling aperture. The cooling aperture is arranged such that cooling fluid impinges on the cooling surface at an angle.
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公开(公告)号：US20210062666A1
公开(公告)日：2021-03-04
申请号：US16550363
申请日：2019-08-26
Applicant: General Electric Company
Inventor： Kevin Robert Feldmann , Robert Proctor , David Scott Stapleton , Robert Charles Groves, II
Abstract: An assembly for a turbine engine comprising a plurality of circumferentially arranged segments having first and second confronting end faces. The first and second confronting end faces include a multi-channel spline seal assembly. The multi-channel spline seal assembly includes at least a first and second channel wherein confronting first or second channels can receive at least one spline seal.
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公开(公告)号：US20200182059A1
公开(公告)日：2020-06-11
申请号：US16210314
申请日：2018-12-05
Applicant: General Electric Company
Inventor： Jeffrey Douglas Rambo , Kirk Douglas Gallier , Brandon Wayne Miller , Craig Alan Gonyou , Kevin Robert Feldmann , Justin Paul Smith
Abstract: An aspect of the present disclosure is directed to a rotor assembly for a turbine engine. The rotor assembly includes an airfoil assembly and a hub to which the airfoil assembly is attached. A wall assembly defines a first cavity and a second cavity between the airfoil assembly and the hub. The first cavity and the second cavity are at least partially fluidly separated by the wall assembly. The first cavity is in fluid communication with a flow of first cooling fluid and the second cavity is in fluid communication with a flow of second cooling fluid different from the first cooling fluid.
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Patent Agency Ranking
公开(公告)号：US20170218784A1
公开(公告)日：2017-08-03
申请号：US15014057
申请日：2016-02-03
Applicant: General Electric Company
Inventor： Kevin Robert Feldmann , Aaron Ezekiel Smith
CPC classification number: F01D11/005 , F01D9/041 , F05D2220/32 , F05D2240/57 , F05D2250/74 , F05D2250/75 , F16J15/02 , F16J15/46 , F16J15/48 , Y02T50/673
Abstract: Embodiments of the invention relate to a turbine assembly including a shroud assembly and a nozzle assembly axially adjacent to each other which both include confronting radial sides and confronting axial ends. A spline connector having a circumferential portion and an axial portion such that the circumferential portion of the spline connector extends across the axial ends and the axial portion of the spline connector extends across the confronting radial sides.
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公开(公告)号：US20170152749A1
公开(公告)日：2017-06-01
申请号：US14955261
申请日：2015-12-01
Applicant: General Electric Company
CPC classification number: F01D5/186 , C23C28/321 , C23C28/345 , F01D5/288 , F01D9/065 , F05D2230/30 , F05D2230/90 , F05D2260/202 , F05D2300/15 , F05D2300/211 , F05D2300/5024 , F05D2300/6033 , F23R3/007 , F23R3/06 , F23R2900/03042 , Y02T50/672 , Y02T50/676 , Y02T50/6765
Abstract: Engine components are provided for a gas turbine engines that generate a hot combustion gas flow. The engine component can include a substrate constructed from a CMC material and having a hot surface facing the hot combustion gas flow and a cooling surface facing a cooling fluid flow. The substrate generally defines a film hole extending through the substrate and having an inlet provided on the cooling surface, an outlet provided on the hot surface, and a passage connecting the inlet and the outlet. The engine component can also include a coating on at least a portion of the hot surface and on at least a portion of an inner surface defined within the passage.
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公开(公告)号：US11898460B2
公开(公告)日：2024-02-13
申请号：US17836049
申请日：2022-06-09
Applicant: General Electric Company
Inventor： Jonathan Michael Rausch , Zachary Daniel Webster , Kevin Robert Feldmann , Andrew David Perry , Kirk Douglas Gallier , Daniel Endecott Osgood
IPC: F01D5/18
CPC classification number: F01D5/187 , F05D2240/30 , F05D2260/202
Abstract: A turbine engine includes an engine core extending along an engine centerline and includes a compressor section, a combustor, and a turbine section in serial flow arrangement. A temperature sensor is provided within the engine and configured to detect a gas temperature within the engine core. A set of blades is circumferentially arranged in the turbine section. A blade in the set of blades includes an outer wall bounding an interior, a cooling conduit within the interior, and a plurality of film holes fluidly coupled to the cooling conduit.
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公开(公告)号：US20220170383A1
公开(公告)日：2022-06-02
申请号：US17673426
申请日：2022-02-16
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Robert Frederick Bergholz , Jason Randolph Allen , Robert David Briggs , Kevin Robert Feldmann , Curtis Walton Stover , Zachary Daniel Webster , Fernando Reiter
IPC: F01D25/12 , F23R3/00 , F01D5/18 , F23R3/06 , F01D9/04 , F01D11/08 , F02C3/04 , F02C7/18 , F23R3/04
Abstract: An engine component assembly with a first substrate having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface, with the cooling surface being different than the hot surface, a second substrate having a first surface in fluid communication with a cooling fluid supply and a second surface, different from the first surface, facing and spaced from the cooling surface to define at least one interior cavity. At least one cavity is provided within the first substrate defining a cavity surface where at least a portion of the cavity surface is directly opposite the second surface. At least one cooling aperture extending through the second substrate from the first surface to the second surface, and defining a streamline along which a cooling fluid passes from the cooling fluid supply to the at least one interior cavity.
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公开(公告)号：US11021961B2
公开(公告)日：2021-06-01
申请号：US16210314
申请日：2018-12-05
Applicant: General Electric Company
Inventor： Jeffrey Douglas Rambo , Kirk Douglas Gallier , Brandon Wayne Miller , Craig Alan Gonyou , Kevin Robert Feldmann , Justin Paul Smith
Abstract: An aspect of the present disclosure is directed to a rotor assembly for a turbine engine. The rotor assembly includes an airfoil assembly and a hub to which the airfoil assembly is attached. A wall assembly defines a first cavity and a second cavity between the airfoil assembly and the hub. The first cavity and the second cavity are at least partially fluidly separated by the wall assembly. The first cavity is in fluid communication with a flow of first cooling fluid and the second cavity is in fluid communication with a flow of second cooling fluid different from the first cooling fluid.
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