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公开(公告)号：US20190153873A1
公开(公告)日：2019-05-23
申请号：US15820568
申请日：2017-11-22
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Aaron Ezekiel Smith , Matthew Thomas Beyer , Gregory Terrence Garay , Zachary Daniel Webster
Abstract: An airfoil for a turbine engine can include an outer wall bounding an interior and extending in a chord-wise direction between a leading edge and a trailing edge, and also extending radially between a root and a tip. A tip rail including at least one tip cooling cavity can project from the tip, and cooling holes can be provided in the tip rail.
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公开(公告)号：US20190017389A1
公开(公告)日：2019-01-17
申请号：US15648564
申请日：2017-07-13
Applicant: General Electric Company
Inventor： Nicholas William Rathay , Thomas Earl Dyson , Brendon James Leary , Gregory Terrence Garay , Gustavo Adolfo Ledezma , David Wayne Weber , Aaron Ezekiel Smith
IPC: F01D5/18
Abstract: An apparatus and method for cooling an airfoil tip for a turbine engine can include a blade, such as a cooled turbine blade, having a tip rail extending beyond a tip wall (94) enclosing an interior for the airfoil 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 airfoil to cool the tip of the airfoil.
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公开(公告)号：US11885236B2
公开(公告)日：2024-01-30
申请号：US17714629
申请日：2022-04-06
Applicant: GENERAL ELECTRIC COMPANY
CPC classification number: F01D5/187 , F01D5/20 , F01D5/3007 , F05D2240/304 , F05D2240/305 , F05D2240/306 , F05D2240/307 , F05D2240/81 , F05D2260/201 , F05D2260/202
Abstract: An airfoil for a turbine engine includes an outer wall bounding an interior and defining a pressure side and a suction side, the outer wall extending axially between a leading edge and a trailing edge to define a chord-wise direction, and also extending radially between a root and a tip to define a span-wise direction. At least one cooling conduit can be formed in the interior of the airfoil, and a tip rail can project from the tip in the span-wise direction.
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公开(公告)号：US20230393554A1
公开(公告)日：2023-12-07
申请号：US18453746
申请日：2023-08-22
Applicant: General Electric Company
Inventor： Daniel Endecott Osgood , Tingfan Pang , Gregory Terrence Garay , Xi Yang , Daniel Lee Durstock , Steven Robert Brassfield , William Charles Herman
IPC: G05B19/4099 , B29C64/393 , G06F30/10
CPC classification number: G05B19/4099 , B29C64/393 , G06F30/10 , G05B2219/35036 , G05B2219/35134 , G05B2219/49007
Abstract: A method of forming a component that includes identifying an acute angle in an original model that is a virtual model of the component. The acute angle is defined by a first surface and a second surface. The method includes compensating the original model at the acute angle to create a compensated acute angle in a compensated model. The method also includes forming, by additive manufacturing, the component based upon the compensated model, where the formed component is more alike the original model than the compensated model.
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公开(公告)号：US11560803B1
公开(公告)日：2023-01-24
申请号：US17520146
申请日：2021-11-05
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Daniel Endecott Osgood , Kirk Douglas Gallier , Zachary Daniel Webster , Gregory Terrence Garay , Daniel Lee Durstock , Ricardo Caraballo
Abstract: An engine component for a turbine engine having a working airflow separated into a cooling airflow and a combustion airflow, the engine component comprising a wall defining an interior and having an outer surface over which flows the combustion airflow, the outer surface defining a first side and a second side. The engine component further comprising at least one cooling conduit provided in the interior and having conduit sidewalls and a set of cooling passages formed in the wall and fluidly coupling the at least one cooling conduit to the outer surface, at least one of the cooling passages in the set comprising a primary cooling passage portion and a secondary cooling passage portion. A diffusion slot located in the primary cooling passage portion and an impingement zone fluidly coupled to the diffusion slot.
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Patent Agency Ranking
46.发明授权公开(公告)号：US11529672B2
公开(公告)日：2022-12-20
申请号：US17228168
申请日：2021-04-12
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 , B22D29/00 , B28B1/00 , B33Y10/00 , B33Y80/00 , C04B35/622 , B28B7/34
Abstract: A method of forming a cast component and a method of forming a casting mold is described herein. The ceramic core-shell mold includes at least first core portion, a first shell portion, and at least one first cavity between the core portion and the first shell portion. The core-shell mold may be manufactured using an additive manufacturing process and may include an integrated ceramic filter. 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：US11499431B2
公开(公告)日：2022-11-15
申请号：US17142788
申请日：2021-01-06
Applicant: General Electric Company
IPC: F01D5/14 , G06F30/17 , G06F113/06
Abstract: An apparatus and method for forming an engine component for a turbine engine, the engine component comprising a wall bounding an interior; a panel portion defining a portion of the wall, the panel portion comprising: an outer wall; an inner wall spaced from the outer wall to define a wall gap; and a structural segment formed within the wall gap comprising at least one structural element. The method including calculating a factor and adjusting a variable until the factor is between a given range.
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公开(公告)号：US11486259B1
公开(公告)日：2022-11-01
申请号：US17519958
申请日：2021-11-05
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Daniel Endecott Osgood , Kirk Douglas Gallier , Zachary Daniel Webster , Gregory Terrence Garay , Nicholas William Rathay , Daniel Lee Durstock
IPC: F01D5/18
Abstract: An engine component for a turbine engine comprising a wall defining an interior and having an outer surface over which flows the combustion airflow. The outer surface defining a first side and a second side extending between an upstream edge and a downstream edge and extending between a root and a tip. At least one cooling conduit provided in the interior and having conduit sidewalls; a set of cooling passages with at least one of the cooling passages in the set comprising: a first cooling passage portion having a surface outlet opening on the surface; a second cooling passage portion, intersecting the first cooling passage portion, and having an inlet fluidly coupled to the cooling conduit and an intermediate outlet fluidly connecting the second cooling passage portion to the first cooling passage at the intersection. The cooling passage comprising at least one fillet.
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公开(公告)号：US11448076B2
公开(公告)日：2022-09-20
申请号：US17213771
申请日：2021-03-26
Applicant: GENERAL ELECTRIC COMPANY
IPC: F01D5/18
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, at least one cooling hole having an inlet fluidly coupled to the cooling passage and an outlet located along the outer wall.
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公开(公告)号：US20220228493A1
公开(公告)日：2022-07-21
申请号：US17714629
申请日：2022-04-06
Applicant: GENERAL ELECTRIC COMPANY
Abstract: An airfoil for a turbine engine includes an outer wall bounding an interior and defining a pressure side and a suction side, the outer wall extending axially between a leading edge and a trailing edge to define a chord-wise direction, and also extending radially between a root and a tip to define a span-wise direction. At least one cooling conduit can be formed in the interior of the airfoil, and a tip rail can project from the tip in the span-wise direction.
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