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公开(公告)号：US12297749B2
公开(公告)日：2025-05-13
申请号：US18966717
申请日：2024-12-03
Applicant: GENERAL ELECTRIC COMPANY
IPC: F01D5/28
Abstract: A turbine engine comprising a compressor section, combustor section, and turbine section in serial flow arrangement, and defining an engine longitudinal axis. The turbine engine includes an airfoil with an outer wall having a pressure side and a suction side, extending between a root and a tip in a span-wise direction, and extending between a leading edge and a trailing edge in a chord-wise direction. The airfoil includes a woven core, a first bonding layer including a toughened region, and a laminate skin provided exterior of the first bonding layer and bonded to the woven core by the first bonding layer.
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公开(公告)号：US12264597B2
公开(公告)日：2025-04-01
申请号：US18070618
申请日：2022-11-29
Applicant: General Electric Company
Inventor： Gregory Carl Gemeinhardt , Nicholas Joseph Kray , Andreas Mastorakis
Abstract: A component for a gas turbine engine. The component includes a continuous fiber blade including an airfoil extending radially between a root and a tip and a blade attachment feature positioned at or adjacent to the root. The component further includes a platform coupled to the root of the continuous fiber blade. The platform includes a plurality of chopped fibers. Additionally, the component includes a thermoplastic polymer contained in both the continuous fiber blade and the platform. Moreover, the continuous fiber blade and platform are coupled together such that the continuous fiber blade and platform form a monolithic composite body.
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公开(公告)号：US10815798B2
公开(公告)日：2020-10-27
申请号：US15891415
申请日：2018-02-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Gregory Carl Gemeinhardt , Douglas Duane Ward , David William Crall
Abstract: A blade for the fan section of a turbine engine comprising a composite core defining a pressure side and a suction side extending axially between a core leading edge and a core trailing edge defining a chord-wise direction and extending radially between a core root and a core tip defining a span-wise direction and a leading edge strip made of materials with different elasticity and mounted to the core leading edge.
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公开(公告)号：US20200182062A1
公开(公告)日：2020-06-11
申请号：US16213653
申请日：2018-12-07
Applicant: General Electric Company
Inventor： Gregory Carl Gemeinhardt , Douglas Duane Ward , David William Crall , Nicholas Joseph Kray
Abstract: An airfoil that includes an airfoil body having a root and a tip, and convex and concave sides that extend between a leading edge and a trailing edge. The airfoil also includes at least a first cladding element that is attached to the airfoil body. The first cladding element includes a first portion and a second portion. The second portion is configured to separate from the first portion when the first cladding element encounters a force of at least a predetermined amount.
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公开(公告)号：US09835239B2
公开(公告)日：2017-12-05
申请号：US15002691
申请日：2016-01-21
Applicant: General Electric Company
Inventor： Warren Rosal Ronk , Gregory Carl Gemeinhardt
IPC: F16H57/04 , F16H57/032 , B64C27/12
CPC classification number: F16H57/032 , B64C27/12 , F16H57/0412
Abstract: A housing that includes a polymer, a reinforcing material, and a thermally conductive filler. A first housing component is defined by the polymer such that the reinforcing material and a thermally conductive filler are embedded within the polymer. The thermally conductive filler is configured such that heat can be passively conducted through the first housing component. The housing can be configured to be an aircraft gearbox housing.
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Patent Agency Ranking
公开(公告)号：US20170211682A1
公开(公告)日：2017-07-27
申请号：US15002691
申请日：2016-01-21
Applicant: General Electric Company
Inventor： Warren Rosal Ronk , Gregory Carl Gemeinhardt
IPC: F16H57/032 , F16H57/04
CPC classification number: F16H57/032 , B64C27/12 , F16H57/0412
Abstract: A housing that includes a polymer, a reinforcing material, and a thermally conductive filler. A first housing component is defined by the polymer such that the reinforcing material and a thermally conductive filler are embedded within the polymer. The thermally conductive filler is configured such that heat can be passively conducted through the first housing component. The housing can be configured to be an aircraft gearbox housing.
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公开(公告)号：US20160076552A1
公开(公告)日：2016-03-17
申请号：US14487428
申请日：2014-09-16
Applicant: General Electric Company
Inventor： Todd Alan Anderson , Nicholas Joseph Kray , Gregory Carl Gemeinhardt , Michael Harvey Schneider
CPC classification number: B29C70/382 , B29C70/202 , B29D99/0025 , B29K2063/00 , B29K2105/0005 , B29K2105/089 , B29L2031/08 , F01D5/282 , F04D29/324 , F05D2220/36 , F05D2300/224 , F05D2300/44 , F05D2300/6034 , Y02T50/672
Abstract: An airfoil structure is presented. The airfoil structure includes an outer casing substantially surrounding a composite core. The composite core includes a plurality of fiber bands, each of the plurality of fiber bands is placed at a predetermined position and orientation at a time, wherein the plurality of fiber bands are interwoven in an in-plane and out-of-plane orientation by interleaving each of the plurality of fiber bands placed in a plane with one or more of the plurality of fiber bands of an adjacent plane to define an interleaved structure. A method for manufacturing an airfoil structure including the composite core is also presented.
Abstract translation: 提出了一种翼型结构。 翼型结构包括基本上围绕复合芯的外壳。 复合芯包括多个纤维带，多个纤维带中的每一个一次被放置在预定的位置和取向，其中多个纤维带以平面内和面外取向交织在一起，由 将放置在平面中的多个光纤带中的每一个与相邻平面的多个光纤带中的一个或多个交织以定义交织结构。 还提出了一种用于制造包括复合芯的翼型结构的方法。
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18.发明申请COMPOSITE ARTICLE INCLUDING COMPOSITE TO METAL INTERLOCK AND METHOD OF FABRICATION 有权复合材料包括复合材料到金属互连和制造方法公开(公告)号：US20140322482A1
公开(公告)日：2014-10-30
申请号：US13872317
申请日：2013-04-29
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Shatil Sinha , Scott Roger Finn , Nicholas Joseph Kray , Peggy Lynn Baehmann , Dong Jin Shim , Gregory Carl Gemeinhardt
IPC: B32B7/08
CPC classification number: B32B7/08 , B29C37/0082 , B29C70/72 , B29C70/745 , B29C70/86 , B29K2705/00 , B29L2031/08 , B29L2031/7504 , Y10T428/19 , Y10T428/24033 , Y10T428/24331 , Y10T428/249923
Abstract: A composite article including a composite component, a metallic component and one or more interlock components. The composite component including a plurality of composite plies and extending heightwise from a component base to a component tip and lengthwise between spaced apart component first and second edges, the composite. The metallic component including a first surface and a second surface and a plurality of openings formed therein extending from the first surface to the second surface. The metallic component including at least a portion substantially or fully embedded in the composite component. The one or more interlock components is interwoven through one or more of the plurality of openings in the metallic component and extending into and at least partially embedded in the composite component to provide an interlocking system between the composite component and the metallic component. A method of fabrication of a composite article is also provided.
Abstract translation: 一种复合制品，其包括复合部件，金属部件和一个或多个互锁部件。 所述复合部件包括多个复合层，并且从组件底部向组件尖端高度方向延伸，并且在间隔开的组件第一和第二边缘之间纵向延伸。 所述金属部件包括第一表面和第二表面以及形成在其中的从所述第一表面延伸到所述第二表面的多个开口。 所述金属部件包括基本上或完全嵌入所述复合部件中的至少一部分。 一个或多个互锁部件通过金属部件中的多个开口中的一个或多个交织，并延伸到并且至少部分地嵌入在复合部件中，以在复合部件和金属部件之间提供互锁系统。 还提供了一种复合制品的制造方法。
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公开(公告)号：US20250092791A1
公开(公告)日：2025-03-20
申请号：US18966717
申请日：2024-12-03
Applicant: GENERAL ELECTRIC COMPANY
IPC: F01D5/28
Abstract: A turbine engine comprising a compressor section, combustor section, and turbine section in serial flow arrangement, and defining an engine longitudinal axis. The turbine engine includes an airfoil with an outer wall having a pressure side and a suction side, extending between a root and a tip in a span-wise direction, and extending between a leading edge and a trailing edge in a chord-wise direction. The airfoil includes a woven core, a first bonding layer including a toughened region, and a laminate skin provided exterior of the first bonding layer and bonded to the woven core by the first bonding layer.
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公开(公告)号：US20240280026A1
公开(公告)日：2024-08-22
申请号：US18172723
申请日：2023-02-22
Applicant: GENERAL ELECTRIC COMPANY
CPC classification number: F01D5/28
Abstract: A turbine engine comprising a compressor section, combustor section, and turbine section in serial flow arrangement, and defining an engine longitudinal axis. The turbine engine includes an airfoil with an outer wall having a pressure side and a suction side, extending between a root and a tip in a span-wise direction, and extending between a leading edge and a trailing edge in a chord-wise direction. The airfoil includes a woven core, a first bonding layer including a toughened region, and a laminate skin provided exterior of the first bonding layer and bonded to the woven core by the first bonding layer.
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