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公开(公告)号：US20220275757A1
公开(公告)日：2022-09-01
申请号：US17188668
申请日：2021-03-01
Applicant: General Electric Company
Inventor： Jeffrey Douglas Rambo , Brandon Wayne Miller , Kevin Robert Feldmann , Patrick Michael Marrinan , Robert Jon McQuiston
Abstract: A method is provided of controlling a cooled cooling air system for an aeronautical gas turbine engine. The method includes: receiving data indicative of an ambient condition of the aeronautical gas turbine engine, data indicative of a deterioration parameter of the aeronautical gas turbine engine, data indicative of an operating condition of the aeronautical gas turbine engine, or a combination thereof; and modifying a cooling capacity of the cooled cooling air system in response to the received data indicative of the ambient condition of the aeronautical gas turbine engine, data indicative of the deterioration parameter of the aeronautical gas turbine engine, data indicative of an operating condition of the aeronautical gas turbine engine, or the combination thereof.
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公开(公告)号：US11313235B2
公开(公告)日：2022-04-26
申请号：US14659640
申请日：2015-03-17
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Frederick Alan Buck , Robert David Briggs , Gulcharan Singh Brainch , Kevin Robert Feldmann
Abstract: An engine component for a gas turbine engine includes a film-cooled substrate having a hot surface facing hot combustion gas and a cooling surface facing a cooling fluid flow. The substrate includes one or more film holes that have a metering section defining a metering diameter and a diffusing section that defines a hooded length.
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公开(公告)号：US10472972B2
公开(公告)日：2019-11-12
申请号：US14955261
申请日：2015-12-01
Applicant: General Electric Company
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：US20170234140A1
公开(公告)日：2017-08-17
申请号：US15043513
申请日：2016-02-13
Applicant: General Electric Company
CPC classification number: F01D5/187 , F01D5/188 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2240/30 , F05D2250/185 , F05D2260/2212 , F05D2260/607 , Y02T50/676
Abstract: A method and apparatus for an airfoil in a gas turbine engine can include an outer surface bounding an interior. At least one flow channel can be defined among one or more full-length and partial-length ribs to further define a cooling circuit within the airfoil. The cooling circuit can have at least one tip turn at the partial-length rib, having at least on fastback turbulator disposed at least partially within the tip turn.
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公开(公告)号：US20150159871A1
公开(公告)日：2015-06-11
申请号：US14407076
申请日：2013-06-13
Applicant: General Electric Company
Inventor： Shawn Michael Pearson , Robert Frederick Bergholz , Douglas Ray Smith , Frederick Alan Buck , Stephen Mark Molter , Kevin Robert Feldmann
CPC classification number: F23R3/04 , F01D5/186 , F01D9/023 , F01D9/065 , F02K1/822 , F05D2240/11 , F05D2240/81 , F05D2260/202 , F23R3/002 , F23R3/06 , F23R2900/03042 , Y02T50/676
Abstract: A gas turbine engine wall is provided. The wall includes an inner surface and an opposing outer surface having at least one film cooling hole defined therein. The at least one film cooling hole includes an inclined inlet bore that extends from the inner surface and a pair of channels that diverge laterally from an outlet end of the inclined inlet bore. The pair of channels have a substantially constant width and are separated by a ridge to form a boomerang cross-sectional shape.
Abstract translation: 提供燃气涡轮发动机壁。 壁包括内表面和相对的外表面，其中限定有至少一个膜冷却孔。 所述至少一个膜冷却孔包括从内表面延伸的倾斜入口孔和从倾斜入口孔的出口端横向分开的一对通道。 一对通道具有基本上恒定的宽度并且由脊分开以形成回旋形横截面形状。
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Patent Agency Ranking
公开(公告)号：US12286902B2
公开(公告)日：2025-04-29
申请号：US18418909
申请日：2024-01-22
Applicant: General Electric Company
Inventor： Daniel Endecott Osgood , Zachary Daniel Webster , Gregory Terrence Garay , Kevin Robert Feldmann
Abstract: A component for a turbine engine includes a body with an exterior surface abutting a combustion flowpath for a combustion gas flow through the turbine engine, a cooling passage defined within the body, and a trench on the exterior surface. The trench includes a plurality of outlets, and a plurality of cooling holes extending from the cooling passage to the corresponding plurality of outlets.
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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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