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公开(公告)号：US20200156145A1
公开(公告)日：2020-05-21
申请号：US16195089
申请日：2018-11-19
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：US20190218917A1
公开(公告)日：2019-07-18
申请号：US15873301
申请日：2018-01-17
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Gregory Terrence Garay , Tingfan Pang , Helen Ogbazion Gabregiorgish , Zachary Daniel Webster , Steven Robert Brassfield
CPC classification number: F01D5/187 , F01D9/02 , F01D25/12 , F01D25/24 , F05D2260/202 , F05D2260/2212
Abstract: An apparatus and method an engine component for a turbine engine comprising an outer wall bounding an interior and defining a pressure side and an opposing suction side, with both sides extending between a leading edge and a trailing edge to define a chord-wise direction, and extending between a root and a tip to define a span-wise direction, at least one cooling passage located within the interior, a set of cooling holes having an inlet fluidly coupled to the cooling passage, an outlet located on one of the pressure side or suction side, with a connecting passage fluidly coupling the inlet to the outlet.
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公开(公告)号：US10344598B2
公开(公告)日：2019-07-09
申请号：US14958082
申请日：2015-12-03
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Zachary Daniel Webster
Abstract: A component for a gas turbine engine comprises an airfoil having an outer surface. One or more cooling passages can be disposed within the airfoil, having a cooling passage extending along a trailing edge. A plurality of cooling channels can extend from the cooling passage through the trailing edge. At least one flow element and at least one film hole can be disposed in the cooling channel or the trailing edge passage adjacent the cooling channel. The flow element and the film hole can be in a predetermined relationship with one another providing improved flow to the film hole.
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公开(公告)号：US20190085706A1
公开(公告)日：2019-03-21
申请号：US15707464
申请日：2017-09-18
Applicant: General Electric Company
Inventor： Zachary Daniel Webster , Kirk D. Gallier
Abstract: An airfoil assembly for a turbine engine can include a platform having a fore edge, an aft edge axially spaced from the fore edge, and opposing heated and cooled surfaces. An airfoil can extend from the heated surface of the platform, and a cooling cavity can be positioned interiorly of the platform.
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公开(公告)号：US20170370229A1
公开(公告)日：2017-12-28
申请号：US15194855
申请日：2016-06-28
Applicant: General Electric Company
CPC classification number: F01D5/186 , B22C9/00 , B22C13/085
Abstract: An apparatus and method for forming a film hole in an outer wall of an airfoil. The film hole includes a blind opening adjacent the interior of the airfoil and a hole adjacent the exterior of the airfoil. The blind opening fluidly couples to the hole to form the film hole for providing a volume of fluid as a surface cooling film along the exterior of the outer wall.
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Patent Agency Ranking
公开(公告)号：US20170268346A1
公开(公告)日：2017-09-21
申请号：US15073687
申请日：2016-03-18
Applicant: General Electric Company
Inventor： Zachary Daniel Webster
CPC classification number: F01D5/186 , F01D5/288 , F01D9/02 , F05D2220/30 , F05D2230/12 , F05D2230/13 , F05D2230/21 , F05D2230/30 , F05D2230/90 , F05D2240/35 , F05D2250/141 , F05D2250/75 , F05D2260/202 , F05D2300/6033 , F23R3/002 , F23R2900/03042 , Y02T50/672 , Y02T50/673 , Y02T50/676
Abstract: An apparatus and method relating to a film hole of a component of a turbine engine comprising including forming the hole in the component and applying a coating to the component such that the coating fills in portions of the film hole.
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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：US20240401483A1
公开(公告)日：2024-12-05
申请号：US18326684
申请日：2023-05-31
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Kirk Douglas Gallier , Zachary Daniel Webster , Brian Kenneth Corsetti
IPC: F01D5/18
Abstract: An airfoil assembly for a turbine engine which generates a hot fluid flow and provides a cooling fluid flow. The airfoil assembly includes a platform with radially spaced upper and lower walls, the platform extending between a platform leading edge and a platform trailing edge to define an axial direction and extending between a pair of slash faces, an airfoil having an airfoil wall extending radially between a root and a tip to define a span length, the platform wall extending from the airfoil wall proximate the root. A fillet extends between the heated surface and the airfoil wall and defines at least a portion of the root. The airfoil assembly further includes a set of film holes.
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公开(公告)号：US11988109B2
公开(公告)日：2024-05-21
申请号：US17973976
申请日：2022-10-26
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Zachary Daniel Webster , Daniel Endecott Osgood , Kirk Douglas Gallier
CPC classification number: F01D5/187 , F01D5/087 , F05D2240/307 , F05D2260/20 , F05D2260/201 , F05D2260/232
Abstract: An apparatus and method for an engine component for a turbine engine. The engine component having an outer wall defining an interior and extending between a root and a tip to define a radial direction, a tip wall spanning the first side and second sides to close the interior at the tip. A tip rail extending from the tip wall and having an inner tip rail surface, an outer tip rail surface extending from at least one of the first or the second side, and radially terminating in an upper tip rail surface connecting the inner tip rail surface and the outer tip rail surface. A tip rim formed in at least one of the outer surface or the inner tip rail surface and spaced from the upper tip rail surface in the radial direction, and multiple cooling passages formed in the outer wall and fluidly coupling the at least one cooling conduit to the tip rim at corresponding passage outlets.
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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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