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公开(公告)号：US20210239004A1
公开(公告)日：2021-08-05
申请号：US17078330
申请日：2020-10-23
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Gregory Terrence Garay , Zachary Daniel Webster , Kirk D. Gallier
IPC: F01D5/18
Abstract: An apparatus and method regarding an airfoil for a turbine engine, the airfoil comprising an outer wall defining an interior bound by a pressure side and a suction side extending axially between a leading edge and a trailing edge defining a chord-wise direction and extending radially between a root and a tip defining a span-wise direction. The airfoil further comprising at least one cooling passage extending radially within the interior and defining a primary cooling airflow; and at least one cooling hole having an inlet defining a first cross-sectional area, the inlet in communication with the cooling passage, an outlet defining a second cross-sectional area greater than the first cross-sectional area; wherein the primary cooling airflow enters the inlet in a first direction and exits the outlet in a second direction different than the first direction.
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公开(公告)号：US11053814B2
公开(公告)日：2021-07-06
申请号：US16356390
申请日：2019-03-18
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Daniel Endecott Osgood , Jonathan Russell Ratzlaff , Kirk D. Gallier
Abstract: A component for a turbine engine includes a body having an outer surface confronting a combustion air flow path and defining an interior, as well as a first cooling passage having at least a portion supplying cooling air to the interior of the body. The component also includes a cyclone separator having a cooling air inlet, a clean air outlet, and a dirty air outlet.
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公开(公告)号：US11021967B2
公开(公告)日：2021-06-01
申请号：US15477335
申请日：2017-04-03
Applicant: General Electric Company
Inventor： Kirk D. Gallier , Cedric Carlton Lowe
Abstract: An apparatus and method of forming an engine component having an outer wall forming an interior. The interior can be separated into two or more flow paths or flow channels. The two flow paths can be formed by casting having one or more core ties connecting the flow paths during casting. One or more core tie holes can be formed remnant of the core ties during casting in order to fluidly couple the two or more flow paths or flow channels.
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公开(公告)号：US10830053B2
公开(公告)日：2020-11-10
申请号：US15818013
申请日：2017-11-20
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Gregory Terrence Garay , Zachary Daniel Webster , Kirk D. Gallier
IPC: F01D5/18
Abstract: An apparatus and method regarding an airfoil for a turbine engine, the airfoil comprising an outer wall defining an interior bound by a pressure side and a suction side extending axially between a leading edge and a trailing edge defining a chord-wise direction and extending radially between a root and a tip defining a span-wise direction, at least one cooling passage extending radially within the interior and defining a primary cooling airflow, and at least one cooling hole having an inlet in communication with the cooling passage and an outlet in communication with the exterior of the outer wall.
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公开(公告)号：US10801724B2
公开(公告)日：2020-10-13
申请号：US15622730
申请日：2017-06-14
Applicant: General Electric Company
Inventor： Kirk D. Gallier
Abstract: An apparatus and method for minimizing a cross-flow across an engine cooling hole can include a component, such as an airfoil, having an outer wall bounding an interior from an exterior. A cooling passage is formed in the interior of the component for cooling the engine component. A cooling hole or film hole can be provided in the outer wall fluidly coupling the interior to the exterior. The cooling passage can be shaped to minimize cross-flow over the cooling hole at the interior of the component.
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Patent Agency Ranking
公开(公告)号：US20190153870A1
公开(公告)日：2019-05-23
申请号：US15818013
申请日：2017-11-20
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Gregory Terrence Garay , Zachary Daniel Webster , Kirk D. Gallier
IPC: F01D5/18
Abstract: An apparatus and method regarding an airfoil for a turbine engine, the airfoil comprising an outer wall defining an interior bound by a pressure side and a suction side extending axially between a leading edge and a trailing edge defining a chord-wise direction and extending radially between a root and a tip defining a span-wise direction, at least one cooling passage extending radially within the interior and defining a primary cooling airflow, and at least one cooling hole having an inlet in communication with the cooling passage and an outlet in communication with the exterior of the outer wall.
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公开(公告)号：US20180298765A1
公开(公告)日：2018-10-18
申请号：US15487981
申请日：2017-04-14
Applicant: General Electric Company
Inventor： Matthew Thomas Beyer , Gregory Terrence Garay , Kirk D. Gallier , Toby George Darkins, JR.
Abstract: An apparatus and method for a replaceable tip element of an airfoil in a turbine engine. The airfoil has an outer wall defining an interior and including a pressure side and a suction side extending axially between a leading edge and a trailing edge defining a chord-wise direction and extending radially between a root and a tip defining a span-wise direction, with the tip having a replaceable tip element.
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公开(公告)号：US20180223681A1
公开(公告)日：2018-08-09
申请号：US15428722
申请日：2017-02-09
Applicant: General Electric Company
Inventor： Kirk D. Gallier , Robert Charles Groves, II
CPC classification number: F01D25/12 , F01D11/005 , F01D11/24 , F05D2240/11 , F05D2260/201 , F05D2300/6033 , Y02T50/676
Abstract: An apparatus for a shroud assembly for a turbine engine and a method of manufacturing such can include the shroud assembly having one or more shroud segments having an inner face in a circumferential organization around a rotating blade assembly. A near wall cooling passage can be provided in the shroud assembly to cool the inner face of the shroud. The near wall cooling passage can exhaust to a purge cavity, a split line, or at the inner face.
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公开(公告)号：US20170089579A1
公开(公告)日：2017-03-30
申请号：US14870866
申请日：2015-09-30
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Kevin Robert Feldmann , Douglas Ray Smith , Kirk D. Gallier , Daniel Scott Martyn , Rachel Anne Vukoja
CPC classification number: F23R3/007 , F01D5/186 , F01D5/284 , F02C7/12 , F05D2250/611 , F05D2250/711 , F05D2250/712 , F05D2260/202 , F05D2300/6033 , F23R3/002 , F23R2900/03042 , Y02T50/672 , Y02T50/676
Abstract: An engine component for a gas turbine engine generating hot combustion gas flow is provided. The engine component can include a substrate constructed from a CMC material and having a hot surface facing the hot combustion gas flow and a cooling surface facing a cooling fluid flow. The hot combustion gas flow defines an upstream direction and a downstream direction relative to the hot surface. The substrate also defines a film hole extending through the substrate and having an inlet provided on the cooling surface, an outlet provided on the hot surface, and a passage connecting the inlet and the outlet. The passage comprises a metering section; and a diffusing section, with the diffusing section including a shelf, a first outer lobe and a second outer lobe.
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公开(公告)号：US20170089578A1
公开(公告)日：2017-03-30
申请号：US14870829
申请日：2015-09-30
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Kevin Robert Feldmann , Douglas Ray Smith , Kirk D. Gallier , Daniel Scott Martyn , Rachel Anne Vukoja
Abstract: An engine component for a gas turbine engine generating hot combustion gas flow is provided. The engine component can include a substrate constructed from a CMC material and having a hot surface facing the hot combustion gas flow and a cooling surface facing a cooling fluid flow. The substrate defines a film hole extending through the substrate and having an inlet provided on the cooling surface, an outlet provided on the hot surface, and a passage connecting the inlet and the outlet. The engine component also includes a flow conditioning structure provided upstream of the outlet on the hot surface. The flow conditioning structure can include a ridge extending from the hot surface.
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