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公开(公告)号：US20240151147A1
公开(公告)日：2024-05-09
申请号：US17979853
申请日：2022-11-03
Applicant: General Electric Company
Inventor： Gary Willard Bryant, Jr. , Nicholas Joseph Kray , Ming Xie , Elzbieta Kryj-Kos , Douglas Lorrimer Armstrong , Nicholas M. Daggett , Frank Worthoff , Scott Roger Finn
IPC: F01D5/28
CPC classification number: F01D5/282 , F05D2220/32 , F05D2230/60 , F05D2300/603
Abstract: The present disclosure relates to an airfoil assembly for a turbine engine and methods of assembly thereof. The airfoil assembly generally includes a composite airfoil and a spar. The composite airfoil has a pressure side and a suction side extending in an axial direction between a leading edge and a trailing edge defining a chordwise direction and extending radially between a root and a tip defining a spanwise direction and having a span-length. The spar includes a first portion including a first material and a second portion joined at an interface with the first portion. The second portion further includes a second material, different from the first material, joined to the first portion at an interface. The method generally includes joining the first portion with the second portion at the interface; and assembling the spar with the composite airfoil.
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公开(公告)号：US11879355B1
公开(公告)日：2024-01-23
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 , F05D2240/30 , F05D2250/25 , F05D2300/6034 , F05D2300/612
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：US12291974B2
公开(公告)日：2025-05-06
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：US12253006B2
公开(公告)日：2025-03-18
申请号：US18088957
申请日：2022-12-27
Applicant: GENERAL ELECTRIC COMPANY
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：US12286903B2
公开(公告)日：2025-04-29
申请号：US18173989
申请日：2023-02-24
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Benjamin Thomas Van Oflen , Gary Willard Bryant, Jr. , Michael John Franks , Elzbieta Kryj-Kos , Nicholas Joseph Kray , Arthur William Sibbach
Abstract: A turbine engine having a disk and a composite airfoil assembly. The disk having a slot. The composite airfoil assembly having an airfoil portion, a dovetail portion, and a roll snubber. The dovetail portion having a radially inner surface. The roll snubber being provided on the radially inner surface. The radially inner surface spaced from the slot to define a gap therebetween.
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Patent Agency Ranking
公开(公告)号：US12241383B2
公开(公告)日：2025-03-04
申请号：US18173952
申请日：2023-02-24
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Benjamin Thomas Van Oflen , Gary Willard Bryant, Jr. , Nicholas Joseph Kray , Arthur William Sibbach , Michael John Franks , Elzbieta Kryj-Kos
Abstract: A turbine engine having a disk, a composite airfoil assembly and a pitch snubber. The disk having a slot. The composite airfoil assembly having an airfoil portion and a dovetail portion. The dovetail portion having a radially inner surface spaced from the slot to define a gap therebetween. The pitch snubber being provided on one of the slot or the radially inner surface of the dovetail portion.
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公开(公告)号：US11931981B2
公开(公告)日：2024-03-19
申请号：US15882044
申请日：2018-01-29
Applicant: General Electric Company
Inventor： Gary Willard Bryant, Jr. , Phani Nandula
IPC: B29D99/00 , B29C70/22 , B29C70/30 , B29L31/08 , B32B3/14 , B32B5/12 , B32B5/26 , B32B27/08 , F01D5/28 , F04D29/38 , B29K307/04 , B29K309/08 , B64D27/16 , B64D33/02
CPC classification number: B29D99/0025 , B29C70/302 , B32B3/14 , B32B5/12 , B32B5/26 , B32B27/08 , F01D5/282 , F04D29/388 , B29C70/228 , B29K2307/04 , B29K2309/08 , B29L2031/08 , B32B2262/101 , B32B2262/106 , B32B2603/00 , B64D27/16 , B64D33/02 , B64D2033/022 , 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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公开(公告)号：US11795827B1
公开(公告)日：2023-10-24
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 , F05D2230/10 , F05D2230/50 , F05D2250/283 , 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：US12228037B1
公开(公告)日：2025-02-18
申请号：US18527567
申请日：2023-12-04
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Brandon Wayne Miller , Gary Willard Bryant, Jr. , Arthur William Sibbach
Abstract: A guide vane assembly for a nacelle of a gas turbine engine includes a forward vane and an aft vane. The aft vane is located aft of the forward vane and forward of a plurality of fan blades. The forward vane defines a fixed pitch angle and the aft vane is movable between a first pitch angle and a second pitch angle.
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公开(公告)号：US20240287911A1
公开(公告)日：2024-08-29
申请号：US18173989
申请日：2023-02-24
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Benjamin Thomas Van Oflen , Gary Willard Bryant, Jr. , Michael John Franks , Elzbieta Kryj-Kos , Nicholas Joseph Kray , Arthur William Sibbach
CPC classification number: F01D5/3007 , F01D5/282 , F05D2220/32 , F05D2240/24 , F05D2240/30
Abstract: A turbine engine having a disk and a composite airfoil assembly. The disk having a slot. The composite airfoil assembly having an airfoil portion, a dovetail portion, and a roll snubber. The dovetail portion having a radially inner surface. The roll snubber being provided on the radially inner surface. The radially inner surface spaced from the slot to define a gap therebetween.
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