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公开(公告)号：US20250019304A1
公开(公告)日：2025-01-16
申请号：US18350165
申请日：2023-07-11
Inventor： Michal Jasiczek , Shatil Sinha , Hrishikesh Keshavan , Gregory Carl Gemeinhardt , John Harvey Graves , Wendy Wenling Lin
Abstract: A geopolymer composite material includes a geopolymer resin, a fibrous reinforcement material embedded in the geopolymer resin for reinforcing the geopolymer resin, and a protective coating material covering the fibrous reinforcement material embedded in the geopolymer resin to provide a coated fibrous reinforcement material. Further, the geopolymer resin and the coated fibrous reinforcement material are combined together to form a prepreg containing the geopolymer resin being pre-impregnated into the coated fibrous reinforcement material and being curable into a solid matrix.
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公开(公告)号：US12196107B2
公开(公告)日：2025-01-14
申请号：US18172723
申请日：2023-02-22
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：US20230228198A1
公开(公告)日：2023-07-20
申请号：US18070618
申请日：2022-11-29
Applicant: General Electric Company
Inventor： Gregory Carl Gemeinhardt , Nicholas Joseph Kray , Andreas Mastorakis
CPC classification number: F01D5/282 , F02C3/04 , F05D2220/32 , F05D2300/603 , F05D2300/614 , F05D2230/50
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：US20170226867A1
公开(公告)日：2017-08-10
申请号：US15018902
申请日：2016-02-09
Applicant: General Electric Company
Inventor： Phani Nandula , Suresh Subramanian , Nicholas Joseph Kray , Gregory Carl Gemeinhardt
CPC classification number: F01D5/147 , F01D5/282 , F01D21/045 , F02C3/06 , F05D2220/32 , F05D2300/603 , Y02T50/672
Abstract: An airfoil for an aircraft engine is provided. The airfoil may include a plurality of composite plies extending in a chordwise direction from a leading edge to a trailing edge and in a spanwise direction between an airfoil tip and an airfoil base. The airfoil may include at least one discontinuous ply having a first ply segment, a second ply segment, and a butt joint disposed between the first ply segment and the second ply segment. The butt joint may be disposed along a first fragment profile to frangibly attach the first and second ply segments.
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公开(公告)号：US20140161620A1
公开(公告)日：2014-06-12
申请号：US13709559
申请日：2012-12-10
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Scott Roger Finn , Peggy Lynn Baehmann , Dong-Jin Shim , Gregory Carl Gemeinhardt
IPC: F01D5/14
CPC classification number: F01D5/141 , F01D5/282 , F01D5/30 , F05D2300/603 , Y02T50/672 , Y10T428/24017 , Y10T428/24182
Abstract: A composite article including composite component extending heightwise from a component base to a component tip and lengthwise between spaced apart component first and second edges. Component plies having widthwise spaced apart ply first and second sides and ply edges therebetween. Component mounted on a spar which includes a shank extending heightwise into the composite component, tab at upper end of shank and substantially or fully embedded in the composite component, and tab tip. Ply edges of at least a first portion of the plies directly or indirectly contacting or pressing against the tab. Ply edges of at least a second portion of the plies may directly or indirectly contact or press against the tab tip. Ply edges of first portion may press against one or more indented or recessed surfaces in the tab. The composite article may be a composite blade or vane including a composite airfoil.
Abstract translation: 一种复合制品，其包括复合材料部件，该组合部件从部件基部高度地延伸到部件尖端，并且在间隔开的部件第一和第二边缘之间纵向延伸。 组件层具有宽度方向间隔开的第一和第二侧以及它们之间的帘布层边缘。 安装在翼梁上的部件，其包括高度地延伸到复合部件中的柄部，柄部的上端处的突出部，并且基本上或完全嵌入复合部件中以及突出部末端。 层片的至少第一部分的层边缘直接或间接接触或压靠突片。 层片的至少第二部分的层边缘可以直接或间接地接触或压靠突片顶端。 第一部分的层边缘可以压靠突片中的一个或多个凹陷或凹陷的表面。 复合制品可以是包括复合翼型件的复合叶片或叶片。
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Patent Agency Ranking
公开(公告)号：US11286782B2
公开(公告)日：2022-03-29
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：US10450870B2
公开(公告)日：2019-10-22
申请号：US15018902
申请日：2016-02-09
Applicant: General Electric Company
Inventor： Phani Nandula , Suresh Subramanian , Nicholas Joseph Kray , Gregory Carl Gemeinhardt
Abstract: An airfoil for an aircraft engine is provided. The airfoil may include a plurality of composite plies extending in a chordwise direction from a leading edge to a trailing edge and in a spanwise direction between an airfoil tip and an airfoil base. The airfoil may include at least one discontinuous ply having a first ply segment, a second ply segment, and a butt joint disposed between the first ply segment and the second ply segment. The butt joint may be disposed along a first fragment profile to frangibly attach the first and second ply segments.
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公开(公告)号：US20190153876A1
公开(公告)日：2019-05-23
申请号：US15818954
申请日：2017-11-21
Applicant: General Electric Company
Inventor： Gregory Carl Gemeinhardt , Thomas Michael Sutter
Abstract: A high temperature polymer composite includes nanocomposite material, such as carbon nanotubes, dispersed in polymer matrix composite resin interlayer region, which may include bismaleimide or polyamide resin, between fiber containing plies. The nanocomposite material may be in an operating temperature in a range between 400-800 degrees Fahrenheit. Gas turbine engine parts or components such as airfoils, stator vanes, casings, and ducts may be made of the high temperature polymer composite.
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公开(公告)号：US10099434B2
公开(公告)日：2018-10-16
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
IPC: B29C70/38 , F01D5/28 , F04D29/32 , B29C70/20 , B29K105/08 , B29K63/00 , B29K105/00 , B29L31/08 , B29D99/00
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.
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公开(公告)号：US09777579B2
公开(公告)日：2017-10-03
申请号：US13709559
申请日：2012-12-10
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Scott Roger Finn , Peggy Lynn Baehmann , Dong-Jin Shim , Gregory Carl Gemeinhardt
CPC classification number: F01D5/141 , F01D5/282 , F01D5/30 , F05D2300/603 , Y02T50/672 , Y10T428/24017 , Y10T428/24182
Abstract: A composite article including composite component extending heightwise from a component base to a component tip and lengthwise between spaced apart component first and second edges. Component plies having widthwise spaced apart ply first and second sides and ply edges therebetween. Component mounted on a spar which includes a shank extending heightwise into the composite component, tab at upper end of shank and substantially or fully embedded in the composite component, and tab tip. Ply edges of at least a first portion of the plies directly or indirectly contacting or pressing against the tab. Ply edges of at least a second portion of the plies may directly or indirectly contact or press against the tab tip. Ply edges of first portion may press against one or more indented or recessed surfaces in the tab. The composite article may be a composite blade or vane including a composite airfoil.
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