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公开(公告)号：US10563867B2
公开(公告)日：2020-02-18
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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公开(公告)号：US20200024987A1
公开(公告)日：2020-01-23
申请号：US16198015
申请日：2018-11-21
Applicant: General Electric Company
Inventor： Ronald Scott Bunker
Abstract: An engine component assembly for impingement cooling. The engine component assembly includes an engine first component having a cooled surface. The engine first component having a flow path on one side of the cooled surface. A second component is a disposed adjacent to the engine first component between the flow path and the engine first component, and has a plurality of openings forming an array through the second component. The cooling flow path passes through the plurality of openings to cool the cooled surface. The second component having a surface facing the cooled surface of the engine first component. A plurality of discrete cooling features that have at least one wall that has a curved cross-section extend from the second component surface into a gap between and toward the cooled surface of the engine first component and defining an array.
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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：US10415408B2
公开(公告)日：2019-09-17
申请号：US15042674
申请日：2016-02-12
Applicant: General Electric Company
Inventor： Ronald Scott Bunker
Abstract: A component for a gas turbine engine includes a hot side wall, a plurality of connection walls, and a cold side wall. The hot side wall is exposed to a core air flowpath defined by the gas turbine engine. The cold side wall is spaced from the hot side wall and rigidly connected to the hot side wall through the plurality of connection walls. The hot side wall, connection walls, and cold side wall together define a cooling air cavity. The cold side wall defines a thermal stress relief slot for at least partially accommodating a relative thermal expansion between the hot side wall and the cold side wall to reduce an amount of thermal stress within the component during operation of the component.
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公开(公告)号：US10267161B2
公开(公告)日：2019-04-23
申请号：US14960924
申请日：2015-12-07
Applicant: General Electric Company
Inventor： Jared Peter Buhler , Ronald Scott Bunker , Victor Hugo Silva Correia , Brian Kenneth Corsetti
IPC: F01D5/18
Abstract: An airfoil for a gas turbine engine can have an exterior wall and an interior wall, with each wall having a thickness. The walls can intersect to define a corner at the intersection. A cooling passage can be defined by the walls at or near the corner to provide fluid communication between the interior and exterior of the airfoil. A film hole can be disposed in the walls and can have a length and diameter to define a ratio of length to diameter, L/D. An arcuate fillet can be located in the corner to define an effective radius for the fillet. The effective radius can be at least 1.5 times larger than the thicknesses of the walls to provide for an increased length to diameter ratio for the film hole.
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Patent Agency Ranking
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：US20190040746A1
公开(公告)日：2019-02-07
申请号：US15670291
申请日：2017-08-07
Applicant: General Electric Company
Inventor： Robert Charles Groves, II , Ronald Scott Bunker
Abstract: A gas turbine engine turbine blade includes internal structural support radially supporting aerodynamic fairing.Strut radially extends away from root of support. Fairing includes hollow fairing airfoil surrounding strut and extending from fairing platform to blade tip shroud at tip of the fairing airfoil. A support cap attached to radially outer end of strut outwardly restrains fairing. Seal teeth may extend outwardly from the support cap. Internal cooling air flow path may extend radially through support. Fairing may be made from material lighter in weight than the support. Fairing material may be ceramic matrix composite and support material may be metallic. Blades may be mounted in rim of disk by roots disposed in slots through rim. Annular plate mounted to, upstream of, and proximate web of disk defines in part cooling airflow path to slot.
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公开(公告)号：US10088164B2
公开(公告)日：2018-10-02
申请号：US14631929
申请日：2015-02-26
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Jason Randolph Allen , Robert Charles Groves, II , Aaron Ezekiel Smith
Abstract: A hot gas path component for an engine may generally include a substrate extending between an outer surface and an inner surface opposite the outer surface. The outer surface may be configured to be exposed to a hot gas path of the engine. In addition, the substrate may be formed from a non-metallic composite material. The hot gas path component may also include a thermal coating disposed on the inner surface of the substrate. The thermal coating may be applied to the inner surface so as to have a non-uniform distribution along at least a portion of the inner surface, wherein the non-uniform distribution provides for change in a thermal gradient experienced across the hot gas path component between the outer and inner surfaces of the substrate.
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公开(公告)号：US10053987B2
公开(公告)日：2018-08-21
申请号：US14929273
申请日：2015-10-31
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Scott Andrew Weaver , Don Mark Lipkin , John Brian McDermott
CPC classification number: F01D5/187 , B23P15/04 , B23P2700/13 , F01D5/182 , F01D5/186 , F01D5/225 , F01D5/288 , F01D9/041 , F01D25/12 , F01D25/28 , F01D25/30 , F05D2220/32 , F05D2230/90 , F05D2260/202 , F05D2260/203 , F05D2260/204 , F05D2300/611 , Y10T29/4932 , Y10T29/49341 , Y10T29/49982 , Y10T428/13 , Y10T428/24314 , Y10T428/24322 , Y10T428/24521 , Y10T428/24562 , Y10T428/24612 , Y10T428/24636
Abstract: A manufacturing method includes forming one or more grooves in a component that comprises a substrate with an outer surface. The substrate has at least one interior space. Each groove extends at least partially along the substrate and has a base and a top. The manufacturing method further includes applying a structural coating on at least a portion of the substrate and processing at least a portion of the surface of the structural coating so as to plastically deform the structural coating at least in the vicinity of the top of a respective groove, such that a gap across the top of the groove is reduced. A component is also disclosed and includes a structural coating disposed on at least a portion of a substrate, where the surface of the structural coating is faceted in the vicinity of the respective groove.
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公开(公告)号：US10024169B2
公开(公告)日：2018-07-17
申请号：US14633174
申请日：2015-02-27
Applicant: General Electric Company
Inventor： Ronald Scott Bunker
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 downstream of the outlet.
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