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公开(公告)号：US20200332659A1
公开(公告)日：2020-10-22
申请号：US16386972
申请日：2019-04-17
Applicant: General Electric Company
Inventor： Tingfan Pang , Helen Ogbazion Gabregiorgish , Zachary Daniel Webster , Gregory Terrence Garay , Steven Robert Brassfield , Daniel Endecott Osgood
IPC: F01D5/18
Abstract: An airfoil for a turbine engine can include an outer wall bounding an interior and defining a pressure side and a suction side 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. A plurality of outlets and a plurality of scalloped portions can extend proximate the trailing edge.
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公开(公告)号：US10807154B2
公开(公告)日：2020-10-20
申请号：US15377783
申请日：2016-12-13
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Gregory Terrence Garay , Xi Yang
IPC: B22C9/22 , B28B7/34 , B22D29/00 , B22C9/04 , B22C7/02 , B28B1/00 , B33Y10/00 , B33Y80/00 , B29C64/135 , F01D5/18 , F01D9/06 , B29L31/00
Abstract: The present disclosure generally relates to integrated core-shell investment casting molds that provide filament structures corresponding to cooling hole patterns in the surface of the turbine blade or stator vane, including in locations that are inaccessible due to the presence of protrusion patterns. The filament structures also provide a leaching pathway for the core portion after metal casting. The invention also relates to core filaments that can be used to supplement the leaching pathway, for example in a core tip portion of the mold.
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公开(公告)号：US20200157947A1
公开(公告)日：2020-05-21
申请号：US16195048
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 cast component having reduced cross flow linking cavities and method of casting may include a body. The body may define a plurality of internal flow channels. The plurality of internal flow channels may include a first internal flow channel and a second internal flow channel. The cast component may also include a plurality of linking cavities obstructing unintended fluid communication between the first internal flow channel and the second internal flow channel through the plurality of linking cavities.
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公开(公告)号：US20200040743A1
公开(公告)日：2020-02-06
申请号：US16055292
申请日：2018-08-06
Applicant: General Electric Company
Inventor： Daniel Endecott Osgood , Zachary Daniel Webster , Gregory Terrence Garay , Kevin Robert Feldmann
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：US20180347375A1
公开(公告)日：2018-12-06
申请号：US15609488
申请日：2017-05-31
Applicant: General Electric Company
Inventor： Matthew Thomas Beyer , Gregory Terrence Garay , Aaron Ezekiel Smith
Abstract: An apparatus and method for cooling an airfoil tip for a turbine engine can include an airfoil, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the airfoil at the tip. A plurality of cooling holes can be provided in the tip rail at the tip. A flow of cooling fluid can be provided through the cooling holes from the interior of the airfoil to cool the tip of the airfoil.
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Patent Agency Ranking
公开(公告)号：US12168309B2
公开(公告)日：2024-12-17
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
IPC: B22C9/10 , B22C9/06 , B22C9/24 , B28B1/00 , B28B11/24 , B28B17/00 , B33Y10/00 , B33Y40/20 , B33Y50/02 , B33Y80/00
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：US12162063B2
公开(公告)日：2024-12-10
申请号：US17532396
申请日：2021-11-22
Applicant: General Electric Company
Inventor： Xi Yang , Michael Cole , Michael Brown , Gregory Terrence Garay , Tingfan Pang , Brian David Przeslawski , Douglas Gerard Konitzer
IPC: B22C9/10 , B22C7/02 , B22C9/04 , B22C9/22 , B22D29/00 , B28B1/00 , B28B7/34 , B33Y10/00 , B33Y80/00
Abstract: A method of forming a cast component and a method of forming a casting mold. The method is performed by connecting at least one wax gate component to a ceramic core-shell mold. The ceramic core-shell mold includes at least a first core portion, a first shell portion, and a second shell portion, wherein the first shell portion is adapted to interface with at least the second shell portion to form at least one first cavity between the core portion and the first and second shell portions. The core-shell mold may be inspected and assembled prior to connection of the wax gate component. At least a portion of the ceramic core-shell mold and the wax gate component is coated with a second ceramic material. The wax gate component is then removed to form a second cavity in fluid communication with the first cavity.
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公开(公告)号：US20240066590A1
公开(公告)日：2024-02-29
申请号：US18500251
申请日：2023-11-02
Applicant: General Electric Company
Inventor： James Herbert Deines , Brian David Przeslawski , Michael John McCarren , Gregory Terrence Garay , Douglas Gerard Konitzer , Mark Willard Marusko , Xi Yang , Brian Patrick Peterson
IPC: B22D25/02 , B22C1/22 , B22C9/02 , B22C9/10 , B22C9/12 , B22C9/24 , B22C13/08 , B22C13/12 , B22C21/14 , B22D29/00 , B28B1/00 , B29C64/124 , B29C64/129 , B29C64/135 , F01D5/12 , F01D9/04 , G03F7/00 , G03F7/20
CPC classification number: B22D25/02 , B22C1/22 , B22C9/02 , B22C9/10 , B22C9/103 , B22C9/108 , B22C9/12 , B22C9/24 , B22C13/08 , B22C13/12 , B22C21/14 , B22D29/00 , B22D29/001 , B22D29/002 , B28B1/001 , B29C64/124 , B29C64/129 , B29C64/135 , F01D5/12 , F01D9/041 , G03F7/00 , G03F7/20 , F05D2230/21 , Y02P10/25
Abstract: The present disclosure generally relates to partial integrated core-shell investment casting molds that can be assembled into complete molds. Each section of the partial mold may contain both a portion of a core and portion of a shell. Each section can then be assembled into a mold for casting of a metal part. The partial integrated core-shell investment casting molds and the complete molds may be provided with filament structures corresponding to cooling hole patterns on the surface of the turbine blade or the stator vane, which provides a leaching pathway for the core portion after metal casting. The invention also relates to core filaments that can be used to supplement the leaching pathway, for example in a core tip portion of the mold.
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公开(公告)号：US11813669B2
公开(公告)日：2023-11-14
申请号：US17826742
申请日：2022-05-27
Applicant: General Electric Company
Inventor： James Herbert Deines , Brian David Przeslawski , Michael John McCarren , Gregory Terrence Garay , Douglas Gerard Konitzer , Mark Willard Marusko , Xi Yang , Brian Patrick Peterson
IPC: B22D25/02 , B22C9/10 , B22C9/12 , B22C9/02 , B22C9/24 , B22D29/00 , B22C1/22 , F01D9/04 , F01D5/12 , B22C21/14 , B22C13/08 , B29C64/135 , B28B1/00 , B29C64/129 , B22C13/12 , G03F7/00 , B29C64/124 , G03F7/20
CPC classification number: B22D25/02 , B22C1/22 , B22C9/02 , B22C9/10 , B22C9/103 , B22C9/108 , B22C9/12 , B22C9/24 , B22C13/08 , B22C13/12 , B22C21/14 , B22D29/00 , B22D29/001 , B22D29/002 , B28B1/001 , B29C64/124 , B29C64/129 , B29C64/135 , F01D5/12 , F01D9/041 , G03F7/00 , G03F7/20 , F05D2230/21 , Y02P10/25
Abstract: Partial integrated core-shell investment casting molds that can be assembled into complete molds are provided herein. Each section of the partial mold may contain both a portion of a core and portion of a shell. Each section can then be assembled into a mold for casting of a metal part. The partial integrated core-shell investment casting molds and the complete molds may be provided with filament structures corresponding to cooling hole patterns on the surface of the turbine blade or the stator vane, which provides a leaching pathway for the core portion after metal casting. Core filaments that can be used to supplement the leaching pathway, for example in a core tip portion of the mold are also provided herein.
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公开(公告)号：US20230358139A1
公开(公告)日：2023-11-09
申请号：US18104371
申请日：2023-02-01
Applicant: GENERAL ELECTRIC COMPANY
CPC classification number: F01D5/147 , F01D25/12 , F23C7/02 , F01D25/14 , F05D2300/70 , F05D2300/60
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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