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公开(公告)号：US20240409238A1
公开(公告)日：2024-12-12
申请号：US18333005
申请日：2023-06-12
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Feng Zhang , Kmk Genghis Khan , Joanne Morello , Changjie Sun , Jieun Kirtley
IPC: B64F1/28
Abstract: A decision tool models emissions for a sustainable aircraft fuel (SAF) for the lifecycle of the fuel. The decision tool includes a controller module configured to receive data related to at least one fuel pathway for the fuel wherein the fuel pathway considers emissions from initial feedstock production to fuel burn during flight and arrival. The decision tool determines at least one fuel pathway for the fuel used to fuel the aircraft during a flight, models an emission score for the at least one fuel pathway, and then outputs the emission score where a user can purchase the fuel or make other decisions based upon the fuel pathway provided by the decision tool.
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公开(公告)号：US20240229653A9
公开(公告)日：2024-07-11
申请号：US17973085
申请日：2022-10-25
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Sreekar Karnati , Yang Jiao , Changjie Sun , John Matthew Sassatelli , Anthony Poli
CPC classification number: F01D5/286 , F03D1/0675
Abstract: A method of forming an erosion shield for a turbine blade includes depositing a layer of filler material defining an upper surface. The method also includes depositing a layer of erosion-resistant material across the upper surface of the layer of filler material. An interface is defined between the layer of filler material and the layer of erosion-resistant material and has a shape of the upper surface. The method also includes machining the layer of filler material to produce the erosion shield. The erosion shield has the layer of erosion-resistant material, the machined layer of filler material, and the interface defined therebetween. An inner surface of the erosion shield is defined by the machined layer of filler material that is sized and shaped for attaching to a leading edge of the turbine blade. Each of the interface and the inner surface extend a length of the erosion shield.
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公开(公告)号：US20240133299A1
公开(公告)日：2024-04-25
申请号：US17973085
申请日：2022-10-24
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Sreekar Karnati , Yang Jiao , Changjie Sun , John Matthew Sassatelli , Anthony Poli
CPC classification number: F01D5/286 , F03D1/0675
Abstract: A method of forming an erosion shield for a turbine blade includes depositing a layer of filler material defining an upper surface. The method also includes depositing a layer of erosion-resistant material across the upper surface of the layer of filler material. An interface is defined between the layer of filler material and the layer of erosion-resistant material and has a shape of the upper surface. The method also includes machining the layer of filler material to produce the erosion shield. The erosion shield has the layer of erosion-resistant material, the machined layer of filler material, and the interface defined therebetween. An inner surface of the erosion shield is defined by the machined layer of filler material that is sized and shaped for attaching to a leading edge of the turbine blade. Each of the interface and the inner surface extend a length of the erosion shield.
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公开(公告)号：US20230304415A1
公开(公告)日：2023-09-28
申请号：US17702101
申请日：2022-03-23
Applicant: General Electric Company
Inventor： Li Zheng , Nicholas Joseph Kray , Changjie Sun
CPC classification number: F01D11/22 , F01D11/122 , F05D2240/11 , F05D2260/232 , F05D2260/606 , F05D2300/505
Abstract: A gas turbine engine is provided. The gas turbine engine includes: a turbomachine; a fan including a plurality of fan blades rotatably driven by the turbomachine; a nacelle surrounding at least in part the plurality of fan blades of the fan; and a clearance control system including a control ring positioned at least partially within the nacelle, coupled to the nacelle, or both for control of a clearance gap between the plurality of fan blades and the nacelle.
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公开(公告)号：US20230175407A1
公开(公告)日：2023-06-08
申请号：US17541859
申请日：2021-12-03
Applicant: General Electric Company
Inventor： Li Zheng , Nicholas Joseph Kray , Changjie Sun
CPC classification number: F01D5/3007 , F01D9/02 , F01D25/28 , F05D2230/60 , F05D2220/32 , F05D2300/603
Abstract: A system for an outlet guide vane assembly and method of assembly thereof are provided herein. The outlet guide vane assembly generally includes a composite outlet guide vane that includes a monolithic body extending in an axial direction from a base to a top, as well as an anchor bracket. At least one of the base and the top includes a bulbous profile having a thickness in a radial direction that is greater than a thickness of the monolithic body in the radial direction, where the radial direction is orthogonal to the axial direction. The anchor bracket generally includes an anchor base, an engagement slot, and at least one side structure defining the engagement slot.
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Patent Agency Ranking
公开(公告)号：US20230126549A1
公开(公告)日：2023-04-27
申请号：US17511850
申请日：2021-10-27
Applicant: General Electric Company
Inventor： Li Zheng , Nicholas Joseph Kray , Changjie Sun
Abstract: An airfoil for a fan section of a turbine engine may include a fan blade or an outlet guide vane, and an edge guard attached thereto. The edge guard may include a heating conduit disposed within at least a portion of the edge guard. An anti-icing system for a plurality of fan blades or outlet guide vanes may include a fluid supply pathway configured to supply heating fluid to respective ones of a plurality of heating conduits within the edge guards attached to respective ones of a plurality of fan blades and/or to a plurality of outlet guide vanes. The heating fluid may include bleed air from a core air flowpath. A method of inhibiting icing on an airfoil may include flowing a heating fluid into a heating conduit disposed within an edge guard attached to the airfoil and heating the edge guard with the heating fluid.
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7.发明授权公开(公告)号：US11326470B2
公开(公告)日：2022-05-10
申请号：US16722980
申请日：2019-12-20
Applicant: General Electric Company
Inventor： Thomas Earl Dyson , Douglas Glenn Decesare , Changjie Sun
Abstract: A ceramic matrix composite (CMC) component and method of fabrication including a plurality of counterflow elongated functional features. The CMC component includes a plurality of longitudinally extending ceramic matrix composite plies forming a densified body and a plurality of elongated functional features formed therein the densified body. Each of the plurality of functional features is configured longitudinally extending and in alignment with the plurality of ceramic matrix composite plies. Each of the plurality of elongated functional features includes an inlet configured in cross-ply configuration. The plurality of elongated functional features are configured to provide a flow of fluid from a fluid source to an exterior of the ceramic matrix composite component. The plurality of functional features are configured in alternating flow configuration.
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公开(公告)号：US20170254210A1
公开(公告)日：2017-09-07
申请号：US15063048
申请日：2016-03-07
Applicant: General Electric Company
Inventor： Ananda Barua , Neelesh Nandkumar Sarawate , Kenneth Martin Lewis , Changjie Sun , Yu Xie Mukherjee , Sathyanarayanan Raghavan
IPC: F01D5/20
CPC classification number: F01D5/20 , F01D11/08 , F05D2230/10 , F05D2240/307 , F05D2250/75
Abstract: An airfoil for use in a turbomachine includes a pressure sidewall and a suction sidewall coupled to the pressure sidewall. The suction sidewall and the pressure sidewall define a leading edge and a trailing edge, the leading edge and the trailing edge define a chord distance. The airfoil includes a tip portion extending between the pressure sidewall and the suction sidewall. The tip portion includes a planar section and a recessed section. The recessed section extends adjacent to the planar section such that a thickness of the planar section is less than a thickness of the airfoil. The recessed section is offset a predetermined distance from the leading edge and the trailing edge along the chord distance.
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公开(公告)号：US20240133297A1
公开(公告)日：2024-04-25
申请号：US17973198
申请日：2022-10-24
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Ananda Barua , Changjie Sun , Christopher Edward Wolfe , John Matthew Sassatelli
CPC classification number: F01D5/005 , B23P6/007 , F05D2230/10 , F05D2230/22
Abstract: A method of manufacturing an erosion-shielded turbine blade includes providing a turbine blade for use with a rotary machine. The turbine blade includes an airfoil extending between a root and a tip. The airfoil includes a pressure side and an opposite suction side, and each of the pressure and suction sides extends between a leading edge and a trailing edge. The method also includes printing a green body part by an additive manufacturing process by selectively depositing a binder solution across a particulate erosion-resistant material, and sintering the green body part to produce a post-sintering erosion shield that includes densified erosion-resistant material. The method also includes coupling the erosion shield to the leading edge of the turbine blade.
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10.发明申请公开(公告)号：US20210189902A1
公开(公告)日：2021-06-24
申请号：US16723011
申请日：2019-12-20
Applicant: General Electric Company
Inventor： Thomas Earl Dyson , Daniel Gene Dunn , Changjie Sun , Christopher Jon Potokar , Douglas Glenn Decesare
Abstract: A ceramic matrix composite (CMC) component and method of fabrication including one or more elongate functional features formed in multiple fiber plies of the CMC component. The CMC component includes a plurality of longitudinally extending ceramic matrix composite plies in a stacked configuration. Each of the one or more elongate functional features includes an inlet and an outlet to provide a flow of fluid from a fluid source to an exterior of the ceramic matrix composite component. The one or more elongate functional features are configured in multiple plies of the plurality of longitudinally extending ceramic matrix composite plies to form a plurality of cooling channels in multiple plies of the ceramic matrix composite component.
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