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公开(公告)号：US11846192B1
公开(公告)日：2023-12-19
申请号：US18304708
申请日：2023-04-21
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Ming Xie , Mitchell Harold Boyer , Tod Winton Davis
CPC classification number: F01D5/3023 , F01D5/282 , F01D5/32 , F05D2230/60 , F05D2260/37 , F05D2300/603
Abstract: An airfoil assembly and a method of forming the airfoil assembly, the airfoil assembly having a trunnion, a spar, and a set of inserts. The trunnion having a flared socket with an open top. The spar extending from the flared socket and through the open top. The spar having a first end located within the flared socket.
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公开(公告)号：US20240352862A1
公开(公告)日：2024-10-24
申请号：US18304784
申请日：2023-04-21
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Tod Winton Davis , Nicholas Mark Daggett , Arthur William Sibbach , Elzbieta Kryj-Kos
CPC classification number: F01D5/3023 , F01D5/282 , F01D5/32 , F05D2260/37 , F05D2300/603
Abstract: An airfoil assembly having a trunnion and a spar. The trunnion having an interior surface defining a flared socket with an open top. The spar extending from the flared socket and through the open top. The spar further having a furcated tail with a set of branches defining an intervening gap between adjacent branches of the set of branches
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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：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：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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Patent Agency Ranking
公开(公告)号：US20170268349A1
公开(公告)日：2017-09-21
申请号：US15074180
申请日：2016-03-18
Applicant: General Electric Company
Inventor： Gary Willard Bryant, JR. , Tod Winton Davis , Wei Wu
Abstract: An airfoil includes: an airfoil body having convex and concave sides extending between a leading edge and a trailing edge, the airfoil body including primary and secondary regions having differing physical properties; and at least one metallic cladding element attached to the airfoil body.
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7.发明申请公开(公告)号：US20150184527A1
公开(公告)日：2015-07-02
申请号：US14418534
申请日：2013-06-28
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Dong-Jin Shim , Tod Winton Davis
CPC classification number: F01D5/26 , C22C19/057 , C22C38/02 , C22C38/04 , C22C38/42 , C22C38/48 , C22C38/54 , F01D5/147 , F01D5/282 , F01D5/288 , F04D29/023 , F04D29/324 , F05D2220/36 , F05D2240/303 , F05D2300/171 , F05D2300/175 , Y02T50/672 , Y10T29/49337
Abstract: A metallic leading edge protective strip adapted to provide impact protection for a leading edge of an airfoil of a turbomachine. The protective strip is formed of a stainless steel or a nickel-based alloy and is denser and provides increased strength and elasticity characteristics as compared to an identical protective strip formed of a titanium-based alloy. The protective strip is particularly suitable for use with composite blades and allows for thinner airfoils, thereby improving engine efficiency.
Abstract translation: 一种金属前缘保护条，适用于为涡轮机的翼型的前缘提供冲击保护。 与由钛基合金形成的相同的保护带相比，保护条由不锈钢或镍基合金形成并且更致密，并提供增强的强度和弹性特性。 保护条特别适合与复合叶片一起使用，并允许更薄的翼型件，从而提高发动机效率。
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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：US20240401486A1
公开(公告)日：2024-12-05
申请号：US18328856
申请日：2023-06-05
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Tod Winton Davis , Elzbieta Kryj-Kos , Michael John Franks
Abstract: A composite airfoil assembly for a gas turbine engine, the composite airfoil assembly comprising a composite airfoil, a first cladding, and a second cladding. The composite airfoil having a core comprising a composite structure having a core bulk modulus and a laminate skin applied to at least a portion of an exterior of the core. The first cladding and the second cladding are coupled to an outer surface of the composite airfoil.
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公开(公告)号：US10774679B2
公开(公告)日：2020-09-15
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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