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公开(公告)号：US10436038B2
公开(公告)日：2019-10-08
申请号：US15162687
申请日：2016-05-24
Applicant: General Electric Company
Inventor： Jared Peter Buhler , Ronald Scott Bunker , Victor Hugo Silva Correia , Brian Kenneth Corsetti
Abstract: An airfoil for a gas turbine engine includes 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. A tip shelf can be defined in the pressure or suction sidewalls. A film hole can extend to the tip shelf, such that the film hole can be shaped to direct a flow of cooling fluid to the film hole to improve film cooling at the tip shelf.
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公开(公告)号：US10428664B2
公开(公告)日：2019-10-01
申请号：US14884134
申请日：2015-10-15
Applicant: General Electric Company
Inventor： Hojjat Nasr , Ronald Scott Bunker , Gregory Michael Laskowski , Erich Alois Krammer
Abstract: A nozzle assembly for a gas turbine engine includes at least one pair of fixed vanes to define a nozzle between the pair of fixed vanes. The vanes can have an interior chamber defining a cooling circuit with a particle separator located within the interior chamber. The particle separator, which can comprise a virtual impactor, can have an accelerator for accelerating fluid moving through the virtual impactor such that the flow path is divided into a major flow moving into the interior chamber and a minor flow moving into a particle collector defined within the virtual impactor. The accelerator accelerates the fluid such that particles within the fluid are carried by their momentum into the particle collector with the minor flow, removing the particles from the major flow of fluid moving into the interior chamber.
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公开(公告)号：US10422235B2
公开(公告)日：2019-09-24
申请号：US14713110
申请日：2015-05-15
Applicant: General Electric Company
Inventor： Ronald Scott Bunker
Abstract: An engine component assembly is provided with an insert having cooling features. The engine component comprises a cooled engine component surface having a flow path on one side thereof and a second component adjacent to the first component. The second component, for example an insert, 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. The second engine component has a plurality of discrete cooling features disposed on a surface facing the first component and near the plurality of cooling openings.
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公开(公告)号：US10408075B2
公开(公告)日：2019-09-10
申请号：US15238233
申请日：2016-08-16
Applicant: General Electric Company
Inventor： Ronald Scott Bunker
Abstract: An apparatus relating to a rim seal for turbine engine comprising a wing and discourager extending into a cavity to form a labyrinth fluid path. The wing and discourager can each include a radial extension. Cooling air can pass through the rim seal along the labyrinth fluid path to resist the ingestion of hot gas from a mainstream flow.
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公开(公告)号：US10344598B2
公开(公告)日：2019-07-09
申请号：US14958082
申请日：2015-12-03
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Zachary Daniel Webster
Abstract: A component for a gas turbine engine comprises an airfoil having an outer surface. One or more cooling passages can be disposed within the airfoil, having a cooling passage extending along a trailing edge. A plurality of cooling channels can extend from the cooling passage through the trailing edge. At least one flow element and at least one film hole can be disposed in the cooling channel or the trailing edge passage adjacent the cooling channel. The flow element and the film hole can be in a predetermined relationship with one another providing improved flow to the film hole.
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Patent Agency Ranking
公开(公告)号：US20190145265A1
公开(公告)日：2019-05-16
申请号：US16247711
申请日：2019-01-15
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：US10161310B2
公开(公告)日：2018-12-25
申请号：US15012173
申请日：2016-02-01
Applicant: GENERAL ELECTRIC COMPANY
Inventor： William Paul Minnear , Ronald Scott Bunker , Narendra Digamber Joshi , Andrei Tristan Evulet
Abstract: A turbine power generation system with enhanced stabilization of refractory carbides provided by hydrocarbon from high carbon activity gases is disclosed. The disclosure also includes a method of using high carbon activity gases to stabilize hot gas path components.
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公开(公告)号：US10010937B2
公开(公告)日：2018-07-03
申请号：US14936641
申请日：2015-11-09
Applicant: General Electric Company
Inventor： Ronald Scott Bunker
CPC classification number: B22F5/04 , B22F3/1055 , B22F7/04 , B22F7/08 , B33Y10/00 , B33Y80/00 , F01D5/186 , F05D2260/202 , F23R3/06 , Y02P10/295
Abstract: A method of forming an overhanging structure at a discharge end of a cooling hole that passes through a component. The method includes the step of using an additive manufacturing process to fuse material to a face to build up an edge of the discharge end of the cooling hole to form an overhanging tab.
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公开(公告)号：US09957816B2
公开(公告)日：2018-05-01
申请号：US14717547
申请日：2015-05-20
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Jason Randolph Allen , Ryan Nicholas Porter , Byron Andrew Pritchard , Christopher Joseph Greenwell , Timothy Deryck Stone , Andrew Stephen Pritchard
CPC classification number: F01D5/188 , F01D5/186 , F01D5/189 , F01D9/04 , F01D25/12 , F02C7/18 , F05D2220/32 , F05D2240/35 , F05D2250/38 , F05D2260/201 , F05D2260/202 , F23R3/005 , F23R3/06 , F23R2900/03042 , F23R2900/03044 , Y02T50/676
Abstract: An engine component with particulate mitigation features is provided. The engine component comprises an internal engine component surface having a cooling flow path on one side thereof and a second component adjacent to the first component. The second component, for example an insert, 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：US20180051566A1
公开(公告)日：2018-02-22
申请号：US15238211
申请日：2016-08-16
Applicant: General Electric Company
Inventor： Ronald Scott Bunker
CPC classification number: F01D5/183 , F01D5/187 , F01D5/28 , F01D9/041 , F01D25/12 , F02K3/06 , F05D2220/323 , F05D2230/30 , F05D2240/301 , F05D2240/304 , F05D2240/307 , F05D2250/185 , F05D2260/22141 , F05D2260/232 , Y02T50/671 , Y02T50/673 , Y02T50/676
Abstract: An apparatus and method for cooling an 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 having full-length ribs, partial-length ribs, passages, or channels can define a cooling circuit for providing a flow of cooling fluid through the airfoil. The tip can include a tip cap forming a portion of the cooling circuit.
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