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公开(公告)号：US11655718B2
公开(公告)日：2023-05-23
申请号：US17316026
申请日：2021-05-10
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
CPC classification number: F01D5/187 , F01D5/141 , F01D5/20 , F01D5/3007 , F05D2220/323 , F05D2240/307 , F05D2260/201 , F05D2260/202 , F05D2260/205
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：US11639664B2
公开(公告)日：2023-05-02
申请号：US17837086
申请日：2022-06-10
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Zachary Daniel Webster , Steven Robert Brassfield , Gregory Terrence Garay , Tingfan Pang , Daniel Endecott Osgood
IPC: F01D5/18
Abstract: An airfoil for a turbine engine, comprising an outer wall defining an exterior surface 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, outlets on the exterior surface, and a cooling air supply conduit within the interior and having a supply passage.
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公开(公告)号：US11585224B2
公开(公告)日：2023-02-21
申请号：US16987872
申请日：2020-08-07
Applicant: General Electric Company
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：US11566527B2
公开(公告)日：2023-01-31
申请号：US16223735
申请日：2018-12-18
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Tingfan Pang , Helen Ogbazion Gabregiorgish , Zachary Daniel Webster , Gregory Terrence Garay , Steven Robert Brassfield , Daniel Endecott Osgood
Abstract: A component, such as for a turbine engine, can include an airfoil with an outer wall defining an exterior surface 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. The component can also include at least one cooling passage within the interior.
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公开(公告)号：US20220288673A1
公开(公告)日：2022-09-15
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 , B22C1/22 , B22C9/10 , B22C9/12 , B22C9/02 , B22C9/24 , B22D29/00 , F01D9/04 , F01D5/12 , B22C21/14 , B22C13/08 , B29C64/135 , B28B1/00 , B29C64/129 , B22C13/12 , G03F7/00 , B29C64/124 , G03F7/20
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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Patent Agency Ranking
公开(公告)号：US11384642B2
公开(公告)日：2022-07-12
申请号：US16929936
申请日：2020-07-15
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Zachary Daniel Webster , Steven Robert Brassfield , Gregory Terrence Garay , Tingfan Pang , Daniel Endecott Osgood
IPC: F01D5/18
Abstract: An airfoil for a turbine engine, comprising an outer wall defining an exterior surface 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, outlets on the exterior surface, and a cooling air supply conduit within the interior and having a supply passage.
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公开(公告)号：US11377963B2
公开(公告)日：2022-07-05
申请号：US17183627
申请日：2021-02-24
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Zachary Daniel Webster , Gregory Terrence Garay , Xi Yang , Tingfan Pang , Steven Robert Brassfield
IPC: F01D5/18
Abstract: An apparatus and method for cooling a component for a turbine engine which generates a hot gas flow and provides a cooling fluid flow, the component comprising a body having an outer surface, at least a portion of which is exposed to the hot gas flow to define a hot surface, a cooling cavity located within the body and fluidly coupled to the cooling fluid flow and a pin located within the cooling cavity and defining a cooling hole.
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公开(公告)号：US11359494B2
公开(公告)日：2022-06-14
申请号：US16532787
申请日：2019-08-06
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Daniel Endecott Osgood , Kirk Douglas Gallier , Daniel Lee Durstock , Zachary Daniel Webster , Gregory Terrence Garay
IPC: F01D5/18
Abstract: An apparatus and method for an engine component for a turbine engine comprising an outer wall having an outer surface and bounding an interior, the outer wall defining a pressure side and a suction side, extending axially between a leading edge and a trailing edge to define a chord-wise direction, and extending radially between a root and a tip to define a span-wise direction, at least one cooling supply conduit provided in the interior, and at least one cooling passage fluidly coupling the at least one cooling supply conduit to the outer surface of the outer wall, the at least one cooling passage comprising an outlet opening onto the outer surface along the leading edge, an inlet fluidly coupled to the at least one cooling supply conduit, and a curved passage defining a curvilinear centerline.
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公开(公告)号：US11299998B2
公开(公告)日：2022-04-12
申请号：US17158670
申请日：2021-01-26
Applicant: General Electric Company
Inventor： Ryan Christopher Jones , Daniel Endecott Osgood , Zachary Daniel Webster , Gregory Terrence Garay , Tingfan Pang
Abstract: A turbomachinery sealing apparatus including a first turbomachinery component having a first end face, and a seal extending away from the first end face, the seal being connected to a wall of the component by a tab extending between the wall and the seal.
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公开(公告)号：US11192172B2
公开(公告)日：2021-12-07
申请号：US15636282
申请日：2017-06-28
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 , B22C9/04 , B22C9/24 , B28B1/00 , B33Y10/00 , B33Y80/00 , B22C7/02 , B22C9/22 , B28B7/34
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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