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公开(公告)号：US11840941B2
公开(公告)日：2023-12-12
申请号：US17673084
申请日：2022-02-16
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Lana Maria Osusky , Gustavo A. Ledezma , Daniel Endecott Osgood , Gregory Alexander Natsui
IPC: F01D5/18
CPC classification number: F01D5/187 , F01D5/186 , F05D2200/11 , F05D2200/14 , F05D2200/212 , F05D2200/221 , F05D2260/20 , F05D2260/202 , F05D2260/2214
Abstract: An engine component for a gas turbine engine, the engine component comprising a cooling architecture comprising at least one unit cell having a set of walls with a thickness, the set of walls defining fluidly separate conduits having multiple openings, each of the multiple openings having a hydraulic diameter; wherein the thickness (t) and the hydraulic diameter (DH) relate to each other by an equation:
(
D
H
+
2
t
)
2
(
(
D
H
+
2
t
)
/
D
H
)
1
/
3
to define a performance area factor (PAF).-
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：US20230258091A1
公开(公告)日：2023-08-17
申请号：US17673084
申请日：2022-02-16
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Lana Maria Osusky , Gustavo A. Ledezma , Daniel Endecott Osgood , Gregory Alexander Natsui
IPC: F01D5/18
CPC classification number: F01D5/187 , F05D2260/202 , F05D2260/2214 , F05D2200/11 , F05D2200/14 , F05D2200/221 , F05D2200/212
Abstract: An engine component for a gas turbine engine, the engine component comprising a cooling architecture comprising at least one unit cell having a set of walls with a thickness, the set of walls defining fluidly separate conduits having multiple openings, each of the multiple openings having a hydraulic diameter; wherein the thickness (t) and the hydraulic diameter (DH) relate to each other by an equation:
(
D
H
+
2
t
)
2
(
(
D
H
+
2
t
)
/
D
H
)
1
/
3
to define a performance area factor (PAF).-
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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Patent Agency Ranking
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：US11499433B2
公开(公告)日：2022-11-15
申请号：US16223279
申请日：2018-12-18
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Daniel Endecott Osgood , Zachary Daniel Webster
Abstract: A turbine engine airfoil and method of cooling includes 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 airfoil can also include at least one cooling conduit and an impingement zone located within the at least one cooling conduit.
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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：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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