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21.发明申请公开(公告)号：US20210189902A1
公开(公告)日：2021-06-24
申请号：US16723011
申请日：2019-12-20
Applicant: General Electric Company
Inventor： Thomas Earl Dyson , Daniel Gene Dunn , Changjie Sun , Christopher Jon Potokar , Douglas Glenn Decesare
Abstract: A ceramic matrix composite (CMC) component and method of fabrication including one or more elongate functional features formed in multiple fiber plies of the CMC component. The CMC component includes a plurality of longitudinally extending ceramic matrix composite plies in a stacked configuration. Each of the one or more elongate functional features includes an inlet and an outlet to provide a flow of fluid from a fluid source to an exterior of the ceramic matrix composite component. The one or more elongate functional features are configured in multiple plies of the plurality of longitudinally extending ceramic matrix composite plies to form a plurality of cooling channels in multiple plies of the ceramic matrix composite component.
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22.发明申请公开(公告)号：US20210189901A1
公开(公告)日：2021-06-24
申请号：US16722980
申请日：2019-12-20
Applicant: General Electric Company
Inventor： Thomas Earl Dyson , Douglas Glenn Decesare , Changjie Sun
Abstract: A ceramic matrix composite (CMC) component and method of fabrication including a plurality of counterflow elongated functional features. The CMC component includes a plurality of longitudinally extending ceramic matrix composite plies forming a densified body and a plurality of elongated functional features formed therein the densified body. Each of the plurality of functional features is configured longitudinally extending and in alignment with the plurality of ceramic matrix composite plies. Each of the plurality of elongated functional features includes an inlet configured in cross-ply configuration. The plurality of elongated functional features are configured to provide a flow of fluid from a fluid source to an exterior of the ceramic matrix composite component. The plurality of functional features are configured in alternating flow configuration.
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公开(公告)号：US10933481B2
公开(公告)日：2021-03-02
申请号：US15862927
申请日：2018-01-05
Applicant: General Electric Company
Inventor： Thomas Earl Dyson , Jason Ray Gregg , Nicholas William Rathay
Abstract: Methods of forming a cooling passage on a turbine component having a component wall with an internal surface and an external surface, are disclosed. An opening is formed passing through the component wall and fluidly connecting the internal and external surfaces. The opening includes a metering section extending from the internal surface to a metering end, and a diffuser area extending from the metering end to the external surface. A preformed cap element is added to close a portion of the diffuser area to form the cooling passage with a diffusion section extending from the metering end to the external surface. The preformed metal cap element includes a projection extending internally of the external surface and into the diffusion area to define an internally facing section of the diffusion section. The cooling passage extends through the component wall and fluidly connects the internal surface and the external surface.
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公开(公告)号：US10605098B2
公开(公告)日：2020-03-31
申请号：US15648541
申请日：2017-07-13
Applicant: General Electric Company
Inventor： Thomas Earl Dyson , Nicholas William Rathay , Brendon James Leary , Gregory Terrence Garay , Gustavo Adolfo Ledezma , David Wayne Weber , Aaron Ezekiel Smith
Abstract: An apparatus and method for cooling a blade tip for a turbine engine can include an blade, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the blade at the tip. A plurality of film-holes can be provided in the tip rail. A flow of cooling fluid can be provided through the film-holes from the interior of the blade to cool the tip of the blade.
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公开(公告)号：US10577944B2
公开(公告)日：2020-03-03
申请号：US15667765
申请日：2017-08-03
Applicant: General Electric Company
Inventor： Emily Rosette Clark , James Richard Winka , Daniel Robinson Getsinger , Thomas Earl Dyson , Brian Gene Brzek , James Fredric Wiedenhoefer , William Robb Stewart
Abstract: An apparatus and method for cooling an engine component, such as an airfoil, for a turbine engine including an outer wall separating a cooling fluid flow from a hot fluid flow. A cooling circuit including a cooling passage having opposing sidewalls can be provided in the engine component. At least one turbulator can be provided between the opposing sidewalls, and can include a conduit having an inlet and an outlet passing through the at least one turbulator.
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Patent Agency Ranking
公开(公告)号：US20190003314A1
公开(公告)日：2019-01-03
申请号：US16122536
申请日：2018-09-05
Applicant: General Electric Company
Inventor： Aaron Ezekiel Smith , Metodi Blagoev Zlatinov , Thomas Earl Dyson
IPC: F01D5/18
Abstract: A component is provided and comprises at least one wall comprising a first and a second surface. At least one film cooling hole extends through the wall between the first and second surfaces and has an outlet region at the second surface. The film cooling hole includes a first expansion section being a side diffusion portion and a second expansion section being a layback diffusion portion, wherein the side diffusion portion is upstream and spaced from the layback diffusion portion.
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公开(公告)号：US20180135423A1
公开(公告)日：2018-05-17
申请号：US15354072
申请日：2016-11-17
Applicant: General Electric Company
Inventor： Thomas Earl Dyson , Daniel Getsinger
IPC: F01D5/18
Abstract: An assembly comprises a cooling chamber disposed inside an airfoil of a turbine assembly. The cooling chamber directs cooling air inside the airfoil. The assembly comprises an impingement hole fluidly coupled with the cooling chamber. The impingement hole directs at least some of the cooling air out of the cooling chamber. A double impingement slot cap assembly forms a cover over the impingement hole. The double impingement slot cap assembly directs the cooling air exiting the cooling chamber in the airfoil through the impingement hole along one or more outer surfaces of the airfoil.
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公开(公告)号：US20170130592A1
公开(公告)日：2017-05-11
申请号：US14938261
申请日：2015-11-11
Applicant: General Electric Company
Inventor： Aaron Ezekiel Smith , Metodi Blagoev Zlatinov , Thomas Earl Dyson
IPC: F01D5/18
CPC classification number: F01D5/186 , F05D2260/202 , Y02T50/672 , Y02T50/676
Abstract: A component is provided and comprises at least one wall comprising a first and a second surface. At least one film cooling hole extends through the wall between the first and second surfaces and has an outlet region at the second surface. The film cooling hole includes a first expansion section being a side diffusion portion and a second expansion section being a layback diffusion portion, wherein the side diffusion portion is upstream and spaced from the layback diffusion portion.
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公开(公告)号：US20230349298A1
公开(公告)日：2023-11-02
申请号：US18344144
申请日：2023-06-29
Applicant: General Electric Company
Inventor： Nicholas William Rathay , Thomas Earl Dyson , Brian Brzek
IPC: F01D5/18
CPC classification number: F01D5/189 , F01D5/186 , F05D2240/121 , F05D2240/304 , F05D2250/711 , F05D2260/202 , F05D2260/2212
Abstract: A cooling assembly includes a coolant chamber disposed inside an airfoil of a turbine assembly that directs coolant inside the airfoil. The airfoil extends between a leading edge and a trailing edge along an axial length of the airfoil. Inlet cooling channels are fluidly coupled with the coolant chamber and direct the coolant in a direction toward a trailing edge chamber of the airfoil. The trailing edge chamber is fluidly coupled with at least one inlet cooling channel. The trailing edge chamber is disposed at the trailing edge of the airfoil and includes an inner surface. The inlet cooling channels direct at least a portion of the coolant in a direction toward the inner surface of the trailing edge chamber. One or more outlet cooling channels direct at least a portion of the coolant in one or more directions away from the trailing edge chamber.
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公开(公告)号：US20230278695A1
公开(公告)日：2023-09-07
申请号：US17688085
申请日：2022-03-07
Applicant: General Electric Company
Inventor： Nicholas William Rathay , Gregory Alexander Natsui , Thomas Earl Dyson
Abstract: A leading edge assembly for a hypersonic vehicle is provided. The leading edge assembly includes an outer wall that tapers to a leading edge, the outer wall having a porous region at the leading edge; a coolant supply assembly in fluid communication with the porous region for selectively providing a flow of coolant through the porous region of the outer wall; and an insulation layer disposed between a portion of the coolant supply assembly and the outer wall, wherein the insulation layer is configured to reduce heat transfer between the coolant supply assembly and the outer wall.
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