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公开(公告)号：US20200024965A1
公开(公告)日：2020-01-23
申请号：US16039646
申请日：2018-07-19
Applicant: GENERAL ELECTRIC COMPANY
Inventor： David Alan Frey , Kirk D. Gallier
Abstract: An apparatus and method relating an airfoil for a turbine engine with 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. The airfoil includes a first cooling passage extending in the span-wise direction within the interior and a second cooling passage defining an impingement surface and located proximate the first cooling passage, an interior wall separating the first cooling passage from the second cooling passage, and at least one cooling hole passing through the interior wall.
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公开(公告)号：US20190085705A1
公开(公告)日：2019-03-21
申请号：US15707303
申请日：2017-09-18
Applicant: General Electric Company
Inventor： Zachary Daniel Webster , Daniel Scott Martyn , Aaron Ezekiel Smith , Kirk D. Gallier
Abstract: An apparatus and method relating to a film-hole of a component of a turbine engine. The film-hole can extend from an inlet to an outlet to define a passage. The film-hole can include a laid back section where a coating can be applied. The method can include forming the film-hole in the component and applying the coating to the component to maintain a specific geometry.
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公开(公告)号：US20180363901A1
公开(公告)日：2018-12-20
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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公开(公告)号：US20180363466A1
公开(公告)日：2018-12-20
申请号：US15622643
申请日：2017-06-14
Applicant: General Electric Company
Inventor： Kirk D. Gallier
Abstract: An apparatus and method for a turbine engine for can include an engine component. The engine component can include an interior cooling passage at least partially defining a cooling circuit for passing a flow of cooling fluid through the component. Film holes provide for exhausting a portion of the cooling fluid to an exterior of the component, to form a cooling film along an exterior hot surface of the engine component. A deflector can be position within the cooling passage upstream form the film hole.
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公开(公告)号：US20180283183A1
公开(公告)日：2018-10-04
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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Patent Agency Ranking
公开(公告)号：US12215634B1
公开(公告)日：2025-02-04
申请号：US18515881
申请日：2023-11-21
Applicant: General Electric Company
Inventor： Arthur W. Sibbach , Robert R. Rachedi , Kirk D. Gallier
Abstract: A turbine engine for an aircraft includes a turbo-engine with a core air flow path, a fan having a fan shaft coupled to the turbo-engine to rotate the fan shaft, and a steam system. A combustor is located in the core air flow path to combust fuel and to generate combustion gases. The steam system extracts water from the combustion gases and vaporizes the water to generate steam. The steam system is fluidly coupled to the core air flow path to inject the steam into the core air flow path. The steam system includes a controller configured to determine a water content of the core air upstream of the steam injection location and to change a position of a steam flow control valve to control the flow of the steam into the core air flow path.
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公开(公告)号：US20220106884A1
公开(公告)日：2022-04-07
申请号：US17468834
申请日：2021-09-08
Applicant: General Electric Company
Inventor： Kirk D. Gallier
Abstract: An apparatus and method for a turbine engine for can include an engine component. The engine component can include an interior cooling passage at least partially defining a cooling circuit for passing a flow of cooling fluid through the component. Film holes provide for exhausting a portion of the cooling fluid to an exterior of the component, to form a cooling film along an exterior hot surface of the engine component. A deflector can be position within the cooling passage upstream form the film hole.
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公开(公告)号：US11149555B2
公开(公告)日：2021-10-19
申请号：US15622643
申请日：2017-06-14
Applicant: General Electric Company
Inventor： Kirk D. Gallier
Abstract: An apparatus and method for a turbine engine for can include an engine component. The engine component can include an interior cooling passage at least partially defining a cooling circuit for passing a flow of cooling fluid through the component. Film holes provide for exhausting a portion of the cooling fluid to an exterior of the component, to form a cooling film along an exterior hot surface of the engine component. A deflector can be position within the cooling passage upstream form the film hole.
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公开(公告)号：US20200300266A1
公开(公告)日：2020-09-24
申请号：US16356544
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 a wall separating a combustion air flow path from a cooling air flow path. The component can include an isolation chamber formed in the cooling air flow path. The component can also include at least one cyclone separator having a cooling air inlet fluidly coupled to the cooling air flow path.
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公开(公告)号：US20200300114A1
公开(公告)日：2020-09-24
申请号：US16356390
申请日：2019-03-18
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Daniel Endecott Osgood , Jonathan Russell Ratzlaff , Kirk D. Gallier
IPC: F01D25/12
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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