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公开(公告)号：US10280760B2
公开(公告)日：2019-05-07
申请号：US14870853
申请日：2015-09-30
Applicant: General Electric Company
Inventor： Narendra Digamber Joshi , Christian Lee Vandervort , Krishan Lal Luthra , Ronald Scott Bunker , Joel Meier Haynes , Venkat Eswarlu Tangirala
IPC: F02C1/00 , F02C3/34 , F02C1/08 , F01D5/18 , F23R3/00 , F02C6/00 , F02C7/18 , F23C9/08 , F01D25/32
Abstract: A turbine assembly is provided. The turbine assembly includes a gas turbine engine including at least one hot gas path component formed at least partially from a ceramic matrix composite material. The turbine assembly also includes a treatment system positioned to receive a flow of exhaust gas from the gas turbine engine. The treatment system is configured to remove water from the flow of exhaust gas to form a flow of treated exhaust gas, and to channel the flow of treated exhaust gas towards the at least one hot gas path component. The at least one hot gas path component includes a plurality of cooling holes for channeling the flow of treated exhaust gas therethrough, such that a protective film is formed over the at least one hot gas path component.
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公开(公告)号：US10227876B2
公开(公告)日：2019-03-12
申请号：US14960991
申请日：2015-12-07
Applicant: General Electric Company
Inventor： Jared Peter Buhler , Ronald Scott Bunker , Victor Hugo Silva Correia , Brian Kenneth Corsetti
Abstract: A blade for a gas turbine engine comprises an airfoil having a pressure side and a suction side, with a root and a tip wall. The pressure side and suction side extend beyond the tip wall to define a tip channel, defining a plurality of internal and external corners. The corners comprise fillets to define a thickness being greater than the thickness for the pressure, suction, or tip walls. A film hole can extend through the fillet, such that the length of the film hole at the fillet can be increased to define an increased length-to-diameter ratio for the film hole to improve film cooling through the film hole.
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公开(公告)号：US10221693B2
公开(公告)日：2019-03-05
申请号：US14901450
申请日：2014-07-03
Applicant: General Electric Company
Inventor： George Joe-Kueng Chan , Ronald Scott Bunker , Victor Hugo Silva Correia , Christopher Kanoa Hoffman
Abstract: An airfoil comprises at least one wall defining a leading edge, a trailing edge, a pressure side extending between the leading edge and the trailing edge, and a suction side extending between the leading edge and the trailing edge. The airfoil is curved in three dimensions and has one or more cavities defined by an interior surface of the at least one wall. A plurality of cooling film holes extending between the cavity and at least one cooling trench located on at least one of the pressure side and the suction side, spaced from the leading edge. The at least one trench has a floor spaced from an outer surface of the airfoil. The plurality of cooling film holes extend through the floor at an angle other than perpendicular.
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公开(公告)号：US10005160B2
公开(公告)日：2018-06-26
申请号：US14720614
申请日：2015-05-22
Applicant: General Electric Company
Inventor： Ronald Scott Bunker
CPC classification number: B23P6/002 , C23C4/00 , C23C28/321 , C23C28/3455 , F01D5/005 , F01D5/187 , F01D5/288 , F02C7/12 , F05D2230/80 , F05D2260/204 , Y02T50/672 , Y02T50/676 , Y02T50/6765 , Y10T29/49721 , Y10T29/49746
Abstract: A method for repairing a component is provided, where the component has a substrate comprising an outer surface and an inner surface and defining one or more grooves. Each groove extends at least partially along the outer surface of the substrate. The component further includes a structural coating, a bond coating, and a thermal barrier coating. The groove(s) and the structural coating define one or more channels for cooling the component. The repair method includes removing the thermal barrier and bond coatings, removing at least a portion of the structural coating in a vicinity of a damaged portion of the component, performing a repair operation on the damaged portion of the component, applying a structural coating at least in a vicinity of the repaired portion of the component, and applying a bond coating and a thermal barrier coating. Additional repair methods are also provided.
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公开(公告)号：US20180051569A1
公开(公告)日：2018-02-22
申请号：US15238277
申请日：2016-08-16
Applicant: General Electric Company
Inventor： Ronald Scott Bunker
CPC classification number: F01D5/186 , F01D5/147 , F01D5/183 , F01D5/187 , F01D9/02 , F01D25/12 , F05D2220/323 , F05D2240/35 , F05D2260/202 , F05D2260/203 , F05D2260/2212 , F05D2300/514 , F05D2300/612 , F23R3/002 , F23R3/06 , F28D1/0246 , F28D2021/0021 , F28D2021/0026 , F28F13/003 , Y02T50/671 , Y02T50/676
Abstract: An apparatus and method for cooling an engine component such as a turbine engine airfoil, including a wall bounding an interior extending axially between a leading edge and a trailing edge and radially between a root and a tip. A cooling circuit it located within the interior of the airfoil can include a porous section having a porosity permitting a volume of fluid, such as air, to pass through the porous section.
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Patent Agency Ranking
公开(公告)号：US20170370221A1
公开(公告)日：2017-12-28
申请号：US15191905
申请日：2016-06-24
Applicant: General Electric Company
Inventor： Ronald Scott Bunker
IPC: F01D5/00 , F01D9/02 , B33Y40/00 , B33Y70/00 , B23P6/04 , C23C24/10 , F01D5/18 , B33Y10/00 , F23R3/00 , B23P6/00 , B33Y50/00
CPC classification number: F01D5/005 , B23P6/007 , B23P6/045 , B33Y10/00 , B33Y40/00 , B33Y50/00 , B33Y70/00 , C23C24/106 , F01D5/186 , F01D9/02 , F05D2230/10 , F05D2230/30 , F05D2230/80 , F05D2240/35 , F05D2260/202 , F05D2300/175 , F23R3/002
Abstract: Methods for repairing a component having a damaged region are provided. The method can include removing the damaged portion from the component to form an intermediate component, wherein the damaged portion has an original geometry; and applying using additive manufacturing a repaired portion onto the intermediate component to form a repaired component. The repaired portion can have a repaired geometry that includes at least one film hole absent in the original geometry, with the film holes being fluidly connected to a cooling supply of the repaired component.
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公开(公告)号：US20170328208A1
公开(公告)日：2017-11-16
申请号：US15150528
申请日：2016-05-10
Applicant: General Electric Company
Inventor： Ronald Scott Bunker
CPC classification number: F01D5/186 , F01D5/288 , F05D2220/323 , F05D2240/306 , F05D2260/202 , F05D2260/204 , F05D2260/205 , F05D2300/611 , Y02T50/676
Abstract: An airfoil for a turbine engine having an engine component including an internal cooling circuit fluidly coupled to a plurality of passages within the outer wall of the engine component where cooling air moves from the internal cooling circuit to an outer surface of the engine component through the passages.
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公开(公告)号：US20170234225A1
公开(公告)日：2017-08-17
申请号：US15043511
申请日：2016-02-13
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Jeremy Clyde Bailey
CPC classification number: F02C7/141 , F01D5/187 , F05D2250/232 , F05D2250/241 , F05D2250/28 , F05D2250/61 , F05D2260/2212 , F05D2260/607 , F15D1/005 , F16K1/00 , Y02T50/672 , Y02T50/676
Abstract: An apparatus and method for an engine component having a hot surface adjacent a hot combustion gas flow and a cooling surface adjacent a cooling fluid flow can include at least one dimple for enhancing the cooling along the cooling surface. The dimple can be shaped having a head and a tail with the head disposed upstream of the tail to provide for reduced dust collection along the engine component.
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公开(公告)号：US20170234134A1
公开(公告)日：2017-08-17
申请号：US15042635
申请日：2016-02-12
Applicant: General Electric Company
Inventor： Ronald Scott Bunker
Abstract: A component stage for a turbomachine includes a component section. The component section includes a flowpath surface at least partially exposed to a core air flowpath defined by the turbomachine, when the component stage is installed in the turbomachine. The component further includes a plurality of sequentially arranged riblets on the flowpath surface, the plurality of sequentially arranged riblets customized for an anticipated location of the flowpath surface within the turbomachine by defining one or both of a non-uniform geometry or a non-uniform spacing.
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公开(公告)号：US20170191417A1
公开(公告)日：2017-07-06
申请号：US14989290
申请日：2016-01-06
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Robert Frederick Bergholz , Jason Randolph Allen , Robert David Briggs , Byron Andrew Pritchard, JR. , Kevin Robert Feldmann , Curtis Walton Stover , Zachary Daniel Webster , Fernando Reiter , Michael Alan Meade
CPC classification number: F01D5/187 , F01D9/065 , F01D25/12 , F05D2240/11 , F05D2250/21 , F05D2250/22 , F05D2250/23 , F05D2250/232 , F05D2250/241 , F05D2250/27 , F05D2260/201 , F05D2260/2214 , F23R3/005 , F23R2900/03044 , F23R2900/03045 , Y02T50/672 , Y02T50/676
Abstract: An engine component assembly includes a first engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface, and a second engine component having a first surface in fluid communication with a cooling fluid flow and a second surface spaced from the cooling surface to define a space. A cooling aperture extends through the second engine component. A cooling feature extends from the cooling surface of the first engine component, and is oriented relative to the cooling aperture such that the cooling fluid flow is orthogonal and non-orthogonal to different portions of the cooling feature.
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