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公开(公告)号：US20220170383A1
公开(公告)日：2022-06-02
申请号：US17673426
申请日：2022-02-16
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Robert Frederick Bergholz , Jason Randolph Allen , Robert David Briggs , Kevin Robert Feldmann , Curtis Walton Stover , Zachary Daniel Webster , Fernando Reiter
IPC: F01D25/12 , F23R3/00 , F01D5/18 , F23R3/06 , F01D9/04 , F01D11/08 , F02C3/04 , F02C7/18 , F23R3/04
Abstract: An engine component assembly with a first substrate having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface, with the cooling surface being different than the hot surface, a second substrate having a first surface in fluid communication with a cooling fluid supply and a second surface, different from the first surface, facing and spaced from the cooling surface to define at least one interior cavity. At least one cavity is provided within the first substrate defining a cavity surface where at least a portion of the cavity surface is directly opposite the second surface. At least one cooling aperture extending through the second substrate from the first surface to the second surface, and defining a streamline along which a cooling fluid passes from the cooling fluid supply to the at least one interior cavity.
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公开(公告)号：US20200277862A1
公开(公告)日：2020-09-03
申请号：US16869831
申请日：2020-05-08
Applicant: General Electric Company
Inventor： Douglas Gerard Konitzer , Scott Ronald Bunker , Robert David Briggs
Abstract: A method and apparatus for minimizing engine weight for a turbine engine by utilizing one or more discrete protuberances disposed on an engine component wall. The wall can have a nominal thickness to decrease engine weight while the protuberances can provide increased discrete thicknesses for providing one or more cooling holes. The increased thickness at the protuberances provides for an increased thickness to provide sufficient length to increase cooling hole effectiveness.
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公开(公告)号：US10563514B2
公开(公告)日：2020-02-18
申请号：US15314618
申请日：2015-05-29
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Robert David Briggs , Shawn Michael Pearson
Abstract: A structure for disrupting the flow of a fluid is provided, the structure comprising: a first lateral wall and a second lateral wall spaced apart from one another a distance across an X-axis; and a turbulator extending between the first lateral wall and the second lateral wall, the turbulator extending away from the floor. The turbulator includes a first front surface extending between the first lateral wall and the second lateral wall, a second front surface extending between the first lateral wall and the second lateral wall, a first rear surface extending between the first lateral wall and the second lateral wall, the first rear surface extending between the first front surface and the floor, and a second rear surface adjoining the first rear surface and extending between the first lateral wall and the second lateral wall, the second rear surface extending between the second front surface and the floor.
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公开(公告)号：US10132166B2
公开(公告)日：2018-11-20
申请号：US14633167
申请日：2015-02-27
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Robert David Briggs
Abstract: An engine component for a gas turbine engine includes a film-cooled substrate having a hot surface facing hot combustion gas flow and a cooling surface facing a cooling fluid flow. A film hole extends through the substrate to an outlet on the hot surface. A flow conditioning structure is provided upstream of the outlet.
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公开(公告)号：US20170306764A1
公开(公告)日：2017-10-26
申请号：US15138624
申请日：2016-04-26
Applicant: General Electric Company
Inventor： Douglas Gerard Konitzer , Scott Ronald Bunker , Robert David Briggs
CPC classification number: F01D5/186 , F01D5/147 , F01D5/187 , F01D25/002 , F05D2220/323 , F05D2230/20 , F05D2240/30 , F05D2250/185 , F05D2250/232 , F05D2260/202 , F05D2260/22141 , Y02T50/671 , Y02T50/676
Abstract: A method and apparatus for minimizing engine weight for a turbine engine by utilizing one or more discrete protuberances disposed on an engine component wall. The wall can have a nominal thickness to decrease engine weight while the protuberances can provide increased discrete thicknesses for providing one or more cooling holes. The increased thickness at the protuberances provides for an increased thickness to provide sufficient length to increase cooling hole effectiveness.
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Patent Agency Ranking
公开(公告)号：US20170276550A1
公开(公告)日：2017-09-28
申请号：US15078868
申请日：2016-03-23
Applicant: General Electric Company
Inventor： Guanghua Wang , Bin Ma , James Peter DeLancey , K.M.K. Genghis Khan , Carlos Bonilla Gonzalez , Robert David Briggs , Nirm Velumylum Nirmalan
IPC: G01J5/00
CPC classification number: G01J5/0088 , G01J5/0014 , G01J5/0887
Abstract: A temperature measurement system includes at least one temperature measurement probe. The at least one temperature measurement probe includes at least one hollow filament configured to emit thermal radiation in a predetermined and substantially continuous wavelength band at least partially representative of a temperature of the at least one hollow filament. The at least one hollow filament has a first diameter and a first emissivity. The at least one temperature measurement probe also includes at least one thin filament extending within at least a portion of the at least one hollow filament. The at least one thin filament is configured to emit thermal radiation in a predetermined and substantially continuous wavelength band at least partially representative of a temperature of the at least one thin filament. The at least one thin filament has a second emissivity and a second diameter less than the first diameter.
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公开(公告)号：US10690055B2
公开(公告)日：2020-06-23
申请号：US15314490
申请日：2015-05-27
Applicant: General Electric Company
Inventor： Curtis Walton Stover , Jonathan Michael Rausch , Satoshi Atsuchi , Gulcharan Singh Brainch , Robert David Briggs , Ronald Scott Bunker , Ambarish Jayant Kulkarni , Michael Alan Meade , Byron Andrew Pritchard , Robert Proctor
Abstract: Gas turbine engine components are provided which utilize an insert to provide cooling air along a cooled surface of an engine component. The insert provides cooling holes or apertures which face the cool side surface of the engine component and direct cooling air onto that cool side surface. The apertures may be formed in arrays and directed at an oblique or a non-orthogonal angle to the surface of the insert and may be at an angle to the surface of the engine component being cooled. An engine component assembly is provided with counterflow impingement cooling, comprising an engine component cooling surface having a cooling fluid flow path on one side and a second component adjacent to the first component. The second component may have a plurality of openings forming an array wherein the openings extend through the second component at a non-orthogonal angle to the surface of the second component.
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公开(公告)号：US10450874B2
公开(公告)日：2019-10-22
申请号：US15043513
申请日：2016-02-13
Applicant: General Electric Company
Abstract: A method and apparatus for an airfoil in a gas turbine engine can include an outer surface bounding an interior. At least one flow channel can be defined among one or more full-length and partial-length ribs to further define a cooling circuit within the airfoil. The cooling circuit can have at least one tip turn at the partial-length rib, having at least on fastback turbulator disposed at least partially within the tip turn.
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公开(公告)号：US20190106991A1
公开(公告)日：2019-04-11
申请号：US16161724
申请日：2018-10-16
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Robert David Briggs
Abstract: An engine component for a gas turbine engine includes a film-cooled substrate having a hot surface facing hot combustion gas flow and a cooling surface facing a cooling fluid flow. A film hole extends through the substrate to an outlet on the hot surface. A flow conditioning structure is provided upstream of the outlet.
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公开(公告)号：US10174620B2
公开(公告)日：2019-01-08
申请号：US14884075
申请日：2015-10-15
Applicant: General Electric Company
Inventor： Matthew Lee Krumanaker , Weston Nolan Dooley , Steven Robert Brassfield , David Benjamin Helmer , Jeremy Clyde Bailey , Robert David Briggs
Abstract: An airfoil comprises one or more internal cooling circuits. The cooling circuit can further comprise a near wall cooling mesh, fluidly coupling a supply passage to a mesh plenum. The mesh plenum can be disposed adjacent to the external surface of the airfoil having a plurality of film holes extending between the mesh plenum and the external surface of the airfoil. The mesh plenum can further comprise a cross-sectional area sized to facilitate machining of the film holes without damage to the interior of the airfoil.
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