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公开(公告)号：US12215602B2
公开(公告)日：2025-02-04
申请号：US18599486
申请日：2024-03-08
Applicant: General Electric Company
Abstract: A component for a turbine engine comprises a wall having a first wall surface and a second wall surface; and a cooling hole comprising a connecting passage extending between an inlet at the first wall surface and an outlet located at the second wall surface. The connecting passage includes: a metering section extending from the inlet toward the outlet and defining a centerline, and a diffusing section at the outlet defining first and second side walls, a first junction between the first side wall and the metering section and a second junction between the second side wall the metering section, the first side wall extending between the first junction and the outlet, and the second side wall extending between the second junction and the outlet. A metering section distance is measured between the centerline and a metering section wall of the metering section.
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公开(公告)号：US20240175364A1
公开(公告)日：2024-05-30
申请号：US18432818
申请日：2024-02-05
Applicant: GENERAL ELECTRIC COMPANY
CPC classification number: F01D5/147 , F01D25/12 , F01D25/14 , F23C7/02 , F05D2300/60 , F05D2300/70
Abstract: A method of forming a gas turbine engine component, the method including forming a plurality of cooling apertures in a preform structure of the component, the plurality of cooling apertures of the preform structure comprising a first cooling aperture and a second cooling aperture, wherein cross-sectional shapes of the first and second cooling apertures of the preform structure are different from one another, as measured in a same relative plane; and applying a coating to at least a portion of the preform structure to form the component, wherein a cross-sectional shape of the first and second cooling apertures of the component are approximately the same as one another, as measured in the same relative plane.
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公开(公告)号：US11879356B2
公开(公告)日：2024-01-23
申请号：US17852875
申请日：2022-06-29
Applicant: General Electric Company
Inventor： Daniel Endecott Osgood , Zachary Daniel Webster , Gregory Terrence Garay , Kevin Robert Feldmann
CPC classification number: F01D5/186 , F01D1/12 , F01D5/147 , F01D5/284 , F01D11/122 , F01D11/14 , F05D2220/32 , F05D2230/31 , F05D2230/311 , F05D2240/303 , F05D2240/304 , F05D2260/201 , F05D2260/202 , F05D2300/514
Abstract: A component for a gas turbine engine. The component includes a body. The body has an exterior surface abutting a flowpath for the flow of a hot combustion gas through the gas turbine engine. Further, the body defines a cooling passageway within the body to supply cool air to the component. The component includes a leading face and a trailing face defining a trench therebetween on the exterior surface. The body defines a plurality of cooling holes extending between the cooling passageway and a plurality of outlets defined in the trench such that the trench is fluidly coupled to the cooling passageway. Additionally, the leading face and trailing face are each tangent to at least one of the plurality of outlets. The trench directs the cool air along a contour of the component.
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公开(公告)号：US20220362965A1
公开(公告)日：2022-11-17
申请号：US17317151
申请日：2021-05-11
Applicant: General Electric Company
Inventor： Gregory Terrence Garay , Brian David Przeslawski , Xi Yang , Joseph Edward Hampshire
Abstract: A method is provided for casting a component. Accordingly, data indicative of at least one location of a unitary core-shell mold which is susceptible to a stress concentration is received. An additive manufacturing process is employed to form the unitary core-shell mold defining a casting cavity. The unitary core-shell mold includes a shell wall defining an outer component shape and a core wall positioned inward of the shell wall. The core wall defines an inner component shape. The core wall and/or the shell wall defines at least one reinforcement recess adjacent to the at least one location which is susceptible to the stress concentration. Following the forming of the unitary core-shell mold, at least one support member is positioned within the reinforcement recess in contact with the at least one location. With the support member in place, the component is cast within the casting cavity.
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公开(公告)号：US11236625B2
公开(公告)日：2022-02-01
申请号：US15615869
申请日：2017-06-07
Applicant: General Electric Company
Inventor： Matthew Thomas Beyer , Gregory Terrence Garay
Abstract: A method for making a cooled component for a turbine engine includes casting an airfoil assembly having an airfoil with an airfoil cooling passage and extending from a platform with at least one platform cooling passage, and forming a connecting passage between the airfoil cooling air passage and the platform cooling air passage via a tool inserted into a breakout opening in a slashface of the platform.
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Patent Agency Ranking
公开(公告)号：US11235491B2
公开(公告)日：2022-02-01
申请号：US16531731
申请日：2019-08-05
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Xi Yang , Michael Cole , Michael Brown , Gregory Terrence Garay , Tingfan Pang , Brian David Przeslawski , Douglas Gerard Konitzer
IPC: B22C9/04 , B22C9/10 , B28B1/00 , B33Y10/00 , B28B7/28 , F01D5/14 , B22C7/02 , B22C9/08 , B28B7/34 , F01D5/18
Abstract: Integrated core-shell investment casting molds include a filament structure corresponding to a cooling hole pattern in the surface of the turbine blade, stator vane, or shroud.
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公开(公告)号：US11174736B2
公开(公告)日：2021-11-16
申请号：US16224065
申请日：2018-12-18
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Daniel Endecott Osgood , Zachary Daniel Webster , Gregory Terrence Garay , Tingfan Pang , Kirk D. Gallier
Abstract: Aspects generally relate to a method of forming a plexus within an additively-manufactured component. The method includes forming a fluid passage in the plexus by serially forming layers of material along a build direction to form a column defining the fluid passage along a first direction within an interior of a turbine engine component.
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28.发明授权公开(公告)号：US11130170B2
公开(公告)日：2021-09-28
申请号：US15887601
申请日：2018-02-02
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Gregory Terrence Garay , Meredith Dubelman , Xi Yang , Tingfan Pang , Michael Scott Cole , Brian David Przeslawski , Douglas Gerard Konitzer , Nicole Barba , Kirk Gallier , Brian Keith
Abstract: Integrated core-shell investment casting molds that provide tongue or groove structures corresponding, respectively, to groove or tongue structures in the surface of the turbine blade or stator vane, including in locations that are otherwise inaccessible provide a pathway to restrict cooling flow between turbine blades to the flowpath.
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公开(公告)号：US20210220904A1
公开(公告)日：2021-07-22
申请号：US17221911
申请日：2021-04-05
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Daniel Endecott Osgood , Tingfan Pang , Gregory Terrence Garay , Zachary Daniel Webster , Ryan Christopher Jones
Abstract: A leachable casting core and method of manufacture may include a plurality of legs configured to establish a plurality of internal flow channels of a cast component. Tie bars, with a first tie bar end and a second tie bar end opposite thereof, may couple to at least two of the plurality of legs. At least one of the tie bars may be oriented to form a linking cavity within the cast component between the internal flow channels. The linking cavity may serve as an obstruction to fluid communication through the linking cavity.
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公开(公告)号：US11035237B2
公开(公告)日：2021-06-15
申请号：US16793138
申请日：2020-02-18
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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