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公开(公告)号：US20210079808A1
公开(公告)日：2021-03-18
申请号：US16568821
申请日：2019-09-12
Applicant: General Electric Company
Inventor： Daniel Endicott Osgood , Gregory Terrence Garay , Daniel Lee Durstock , Steven Robert Brassfield , Tingfan Pang
Abstract: The disclosure relates to a component for a turbine engine with a heated airflow and a cooling airflow. The component includes a wall separating the heated airflow from the cooling airflow. The wall can have a heated surface confronting the heated airflow and a cooled surface confronting the cooling airflow. The component can also include a baffle with a set of cooling holes.
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公开(公告)号：US10927692B2
公开(公告)日：2021-02-23
申请号：US16055987
申请日：2018-08-06
Applicant: General Electric Company
Inventor： Ryan Christopher Jones , Daniel Endecott Osgood , Zachary Daniel Webster , Gregory T. 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：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：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：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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Patent Agency Ranking
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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公开(公告)号：US20230311199A1
公开(公告)日：2023-10-05
申请号：US17713540
申请日：2022-04-05
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Evin Nathaniel Barber , Joshua L. Miller , Christophe Jude Day , Brian D. Przeslawski , Tingfan Pang , Gregory Terrence Garay , Xi Yang , Meredith Elissa Dubelman , Daniel Endecott Osgood , Ricardo Caraballo , Thomas Hewitt
Abstract: An intermediate investment casting mold includes at least a shell and a core. The shell has an outer surface and an inner surface, with the inner surface defining an interior for the shell. The core is located in the interior of the shell and is at least partially spaced from the inner surface of the shell. A void can be defined as the space between the core and the inner surface. The intermediate investment casting mold can include a plurality of anchors.
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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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