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公开(公告)号：US20240287908A1
公开(公告)日：2024-08-29
申请号：US18173930
申请日：2023-02-24
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Gary Willard Bryant, JR.
CPC classification number: F01D5/282 , F01D5/3007 , F05B2280/6003
Abstract: A composite airfoil assembly comprising a core, a first set of plies, and a second set of plies. The core being formed of multiple composite plies. The first set of plies being formed of multiple composite unidirectional plies. The second set of plies having a radially outermost ply with at least two fibers that are either braided or woven.
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公开(公告)号：US20230313687A1
公开(公告)日：2023-10-05
申请号：US17712701
申请日：2022-04-04
Applicant: General Electric Company
Inventor： Raghuveer Chinta , Srinivas Nuthi , Gary Willard Bryant, JR. , Nicholas Joseph Kray
IPC: F01D5/14
CPC classification number: F01D5/147 , F05D2250/283 , F05D2230/50 , F05D2230/10 , F05D2300/612
Abstract: An airfoil assembly comprising a central spar extending along the radial direction; a blade skin positioned around the central spar to define an airfoil that has a pressure side and a suction side extending in the axial direction between a leading edge and a trailing edge, wherein at least one cavity is defined between the blade skin and the central spar; and a support structure positioned at least partially within the at least one cavity. The support structure comprises: a foam; and a foam reinforcement structure embedded within the foam.
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公开(公告)号：US20240417063A1
公开(公告)日：2024-12-19
申请号：US18333743
申请日：2023-06-13
Applicant: GENERAL ELECTRIC COMPANY
Abstract: A composite airfoil assembly for a gas turbine engine. The composite airfoil assembly includes a composite airfoil defined by a core and a skin. The composite airfoil assembly further includes cladding. The core defines a core exterior, where the skin is applied to at least a portion of the core exterior. The cladding is prepared before being coupled or adhered to the composite airfoil.
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公开(公告)号：US20240271528A1
公开(公告)日：2024-08-15
申请号：US18308105
申请日：2023-04-27
Applicant: General Electric Company
Inventor： Vaishnav Raghuvaran , Bhaskar Nanda Mondal , Gary Willard Bryant, JR.
CPC classification number: F01D5/021 , F01D5/3007 , F01D11/008 , F05D2220/36 , F05D2230/60
Abstract: A fan assembly includes a disk having a disk forward surface, a disk aft surface, and a radially outer surface. The disk defines a plurality of disk posts and a plurality of disk slots in the radially outer surface. At least one of the plurality of disk posts includes a post slot. The fan assembly also includes a fan having a plurality of fan blades and a plurality of platforms extending between adjacent fan blades of the plurality of fan blades. Each of the plurality of fan blades is received within one of the plurality of disk slots via a respective blade root. Further, the fan assembly includes at least one fan retention member having a body portion and a protrusion extending from the body portion. The protrusion is received within the post slot such that the at least one fan retention member supports one of the plurality of platforms.
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公开(公告)号：US20190234420A1
公开(公告)日：2019-08-01
申请号：US15882044
申请日：2018-01-29
Applicant: General Electric Company
Inventor： Gary Willard Bryant, JR. , Phani Nandula
CPC classification number: F04D29/388 , B29C70/228 , B29C70/30 , B29D99/0025 , B29K2307/04 , B29K2309/08 , B29L2031/08 , B32B3/14 , B32B5/12 , B32B5/26 , B32B27/08 , B32B2262/101 , B32B2262/106 , B32B2603/00 , B64D27/16 , B64D33/02 , B64D2033/022 , F01D5/282 , F05D2220/36 , F05D2300/6034
Abstract: A blade is provided. The blade comprises a plurality of a first composite fiber plies and a plurality of a second composite fiber plies. Ends of the second fiber plies are staggered such that interlock between the first composite fiber plies and the second composite fiber plies is formed in a region where the second composite fiber plies end and meet with the first composite fiber plies. The blades are used for an engine of an aircraft.
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Patent Agency Ranking
公开(公告)号：US20250012192A1
公开(公告)日：2025-01-09
申请号：US18348452
申请日：2023-07-07
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Arthur William Sibbach , Nicholas Joseph Kray , Elzbieta Kryj-Kos , Gary Willard Bryant, JR. , Michael John Franks
IPC: F01D5/14
Abstract: A composite airfoil assembly for a turbine engine includes an airfoil defining an airfoil interior, and an inner support structure at least partially located within the airfoil interior. The inner support structure can include a first core, a second core, and at least one pin. A laminate overlay surrounds at least a portion of the inner support structure.
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公开(公告)号：US20240384657A1
公开(公告)日：2024-11-21
申请号：US18318950
申请日：2023-05-17
Inventor： Nicholas Joseph Kray , Nicholas Mark Daggett , Elzbieta Kryj-Kos , Necip Adali , Benjamin Thomas Van Oflen , Gary Willard Bryant, JR. , Douglas Lorrimer Armstrong
IPC: F01D5/14
Abstract: A turbine engine including a fan section, a compressor section, a combustion section, a turbine section, and an airfoil assembly. The airfoil assembly comprising a spar, a trunnion and a stress relief. The trunnion having an upper edge with an open top, and a socket extending from the open top. The spar extending through the open top and into the socket. A junction being formed between the spar and a portion of the upper edge defining the open top.
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公开(公告)号：US20240209741A1
公开(公告)日：2024-06-27
申请号：US18088957
申请日：2022-12-27
Applicant: GENERAL ELECTRIC COMPANY
CPC classification number: F01D5/282 , F01D5/147 , F01D5/3007 , F05D2220/32 , F05D2240/24 , F05D2240/30 , F05D2300/603
Abstract: A composite blade assembly for a turbine engine. The composite blade assembly having a core, a first skin and a second skin. The core having a composite structure. The first skin having at least one composite ply. The second skin having at least one composite ply. The first skin having a first radius. The second skin having a second radius.
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公开(公告)号：US20240044254A1
公开(公告)日：2024-02-08
申请号：US17881771
申请日：2022-08-05
Applicant: General Electric Company
Inventor： David Raju Yamarthi , Vasanth Kumar Balaramudu , Vishnu Vardhan Venkata Tatiparthi , Paul Mathew , Douglas Lorrimer Armstrong , Gary Willard Bryant, JR. , Nuthi Srinivas
CPC classification number: F01D5/147 , F01D5/282 , F05D2250/25 , F05D2240/30 , F05D2300/612 , F05D2300/6034
Abstract: An airfoil assembly and a method of manufacturing the same are provided, the airfoil assembly defining a span axis, a root end, and a tip end. The airfoil assembly includes a reinforcement structure comprising a first helical support structure wrapped around the span axis between the root end and the tip end and a second helical support structure wrapped around the span axis between the root end and the tip end; a polymeric matrix material positioned at least partially around the reinforcement structure; and an outer skin positioned around the reinforcement structure and the polymeric matrix material.
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公开(公告)号：US20200123910A1
公开(公告)日：2020-04-23
申请号：US15892630
申请日：2018-02-09
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Stephanie Glynn Cotten , James Francis Brown , Theodore Robert Ingling , Tod Winton Davis , Gary Willard Bryant, JR. , Max Robert Farson
Abstract: An airfoil assembly for a turbine engine includes an airfoil with an outer wall having a pressure side and a suction side, the airfoil extending axially between a leading edge and a trailing edge to define a chord-wise direction and also extending radially between a root and a tip to define a span-wise direction. An aperture and at least one slot can define at least a portion of a release plane extending through the outer wall.
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