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公开(公告)号：US20180105246A1
公开(公告)日：2018-04-19
申请号：US15295679
申请日：2016-10-17
Applicant: General Electric Company
IPC: B63H1/20
Abstract: An apparatus and system for a propeller assembly are provided. In one aspect, marine propeller assembly includes a plurality of circumferentially-spaced blades that each include a dovetail having a radially inner surface. The marine propeller assembly also includes a hub including a plurality of circumferentially-spaced dovetail receiving portions configured to receive a corresponding dovetail of the plurality of blades. At least one gap is formed between the radially inner surface and at least a portion of the dovetail receiving portion.
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公开(公告)号：US09885244B2
公开(公告)日：2018-02-06
申请号：US14418534
申请日：2013-06-28
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Dong-Jin Shim , Tod Winton Davis
IPC: F01D5/28 , F01D5/26 , F01D5/14 , F04D29/32 , F04D29/02 , C22C19/05 , C22C38/02 , C22C38/04 , C22C38/42 , C22C38/48 , C22C38/54
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.
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公开(公告)号：US20170373612A1
公开(公告)日：2017-12-28
申请号：US15189026
申请日：2016-06-22
Applicant: General Electric Company
Inventor： Aaron Todd Sellinger , Nicholas Joseph Kray
CPC classification number: H02N2/186 , C04B35/117 , C04B35/52 , C04B35/565 , C04B35/80 , C04B2235/3217 , C04B2235/3225 , C04B2235/3244 , C04B2235/3418 , C04B2235/349 , C04B2235/5224 , C04B2235/5228 , C04B2235/5244 , F01D5/10 , F01D5/16 , F01D5/26 , F01D5/282 , F01D15/10 , F01D25/005 , F01D25/04 , F01D25/06 , F03G7/08 , F04D29/388 , F05D2260/407 , F05D2300/6033 , G01K7/02 , G01L1/16 , H01L35/32 , H01L41/113 , H02N2/181 , Y02T50/672 , Y02T50/673
Abstract: The present disclosure is directed to an engine component for a gas turbine engine, the engine component including a substrate that includes a composite fiber and defines a surface. An energy harvesting fiber is positioned within the substrate.
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公开(公告)号：US20170321714A1
公开(公告)日：2017-11-09
申请号：US15148631
申请日：2016-05-06
Applicant: General Electric Company
Inventor： Nitesh Jain , Vikulp Sharma , Nicholas Joseph Kray
Abstract: A metal leading edge includes a nose positioned along the leading edge of a fan blade airfoil body. The metal leading edge also includes a first edge extending axially aftward from the nose along a pressure side of the fan blade airfoil body. The metal leading edge further includes a second edge extending axially aftward from the nose along a suction side of the fan blade airfoil body. The first edge and the second edge forming a notch at the conjunction of the first edge, the second edge, and the nose. The metal leading edge also includes a nose length extending from a nose tip to the notch. The nose length at a first radial location is different from the nose length at a second radial location.
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公开(公告)号：US09797257B2
公开(公告)日：2017-10-24
申请号：US13709651
申请日：2012-12-10
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Scott Roger Finn , Peggy Lynn Baehmann , Joel Primmer White
CPC classification number: F01D5/147 , B29C70/202 , B29C70/38 , B29D99/0025 , B29L2031/082 , F01D5/282 , Y02T50/672
Abstract: A composite article including composite component mounted on a spar including a shank extending heightwise from below component base up into composite component. Tab at an upper end of shank substantially or fully embedded in the composite component and at least one ply surface pattern of the composite component contacting and generally conforming to at least one spar surface pattern on the tab.Spar surface pattern may include spaced apart spar surface protrusions with spar surface spaces therebetween and spar surface protrusions extending outwardly from spar and disposed between tows in ply surface pattern. Tows may be layed up in spar surface spaces. Spar surface pattern may include continuous or segmented spaced spar surface protrusions and spar surface spaces therebetween with tows in ply surface pattern disposed in spar surface spaces. The composite article may be a composite blade or vane including a composite airfoil.
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Patent Agency Ranking
106.发明申请公开(公告)号：US20170268374A1
公开(公告)日：2017-09-21
申请号：US15071264
申请日：2016-03-16
Applicant: General Electric Company
Inventor： Aaron Todd Sellinger , Nicholas Joseph Kray , Wendy Wenling Lin
CPC classification number: F01D17/141 , F01D5/148 , F01D17/10 , F02C7/042 , F02C9/18 , F04D27/0215 , F04D27/023 , F04D29/563 , F05D2220/32 , F05D2250/90 , F05D2270/20 , F05D2270/60 , F05D2270/64 , F05D2270/65 , F05D2300/501 , Y02T50/672 , Y02T50/673
Abstract: A system for actuating components of a gas turbine engine may generally include a turbine component incorporating a jamming device. The jamming device may include a bladder and a jammable media contained within the bladder. The jammable media may be jammable within the bladder from an unjammed state, wherein a fluid is contained within the bladder, to a jammed state, wherein the fluid is at least partially evacuated from the bladder. The system may also include a fluid coupling in fluid communication with the bladder. A portion of the turbine component may be located at a first position when the jammable media is in the unjammed state. Additionally, such portion of the turbine component may be located at a second position when the jammable media is in the jammed state.
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公开(公告)号：US20170226865A1
公开(公告)日：2017-08-10
申请号：US15040582
申请日：2016-02-10
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Trevor Howard Wood , Dong-Jin Shim , Pranav Dhoj Shah
CPC classification number: F01D5/141 , F01D5/147 , F01D5/282 , F01D5/288 , F01D9/041 , F05D2220/323 , F05D2240/121 , F05D2240/303 , F05D2250/184 , F05D2250/29 , F05D2300/10 , F05D2300/603 , Y02T50/672 , Y02T50/673
Abstract: An airfoil assembly including a composite body having a mounting edge and a trailing edge which is secured to a leading edge element defining a 3-D leading edge geometry with both chord and camber variation.
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公开(公告)号：US20170167502A1
公开(公告)日：2017-06-15
申请号：US14968306
申请日：2015-12-14
Applicant: General Electric Company
Inventor： Todd Alan Anderson , Nicholas Joseph Kray , Bryant Edward Walker
CPC classification number: F04D29/322 , F01D5/3023 , F04D29/324 , F04D29/644 , F05B2220/302 , F05B2230/60 , F05B2260/30 , F05D2220/36 , F05D2260/31
Abstract: A rotor assembly for use in a turbofan engine is provided. The rotor assembly includes an annular spool including a first blade opening defined therein, a first rotor blade configured to be radially inserted through the first blade opening, and a fairing positioned on a radially outer side of the annular spool. The first rotor blade includes a blade portion and a flange portion that extends substantially perpendicularly relative to the blade portion such that the flange portion is positioned on a radially inner side of the annular spool. The fairing is configured to receive a fastener radially inserted through the flange portion and the annular spool such that the first rotor blade is secured to the annular spool.
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公开(公告)号：US20170146020A1
公开(公告)日：2017-05-25
申请号：US14945670
申请日：2015-11-19
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Todd Alan Anderson
CPC classification number: F01D5/30 , F01D5/282 , F01D5/3023 , F01D5/303 , F01D5/3092 , F05D2300/603
Abstract: A rotor assembly for use in a turbofan engine is provided. The rotor assembly includes an annular spool including a blade opening defined therein, and a rotor blade radially insertable through the blade opening. The rotor blade includes a rotor blade radially insertable through the blade opening. The rotor blade includes a root portion having a dovetail shape, and the root portion is undersized relative to the blade opening. At least one secondary dovetail member is positioned within the blade opening and configured to couple the root portion within the blade opening with an interference fit.
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110.发明申请公开(公告)号：US20160179984A1
公开(公告)日：2016-06-23
申请号：US14579200
申请日：2014-12-22
Applicant: General Electric Company
Inventor： Teresa Tianshu Chen-Keat , Li Zheng , Nicholas Joseph Kray , Pinghai Yang , Ruben Egberto Fairman , Michael Scott Hartle
CPC classification number: G06T17/00 , B29C70/30 , G06F17/5018 , G06F2217/44
Abstract: A method for generating a computer model of a composite component includes generating a surface mesh based on a ply drop region and a ply curved surface and generating node data including a plurality of node points relative to the ply drop region. The method also includes receiving composite data relating to a plurality of composite plies and generating a three dimensional model based on the composite data. The method further includes receiving layup table information and applying the node data, based on the layup table information, to generate a curve through a center of the surface mesh to define a plurality of element sets. The method also includes receiving composite draping data and determining, based on the draping data, where each element set intersects the three dimensional model. The method also includes analyzing an angle deviation of the plies based on the intersection of the element sets.
Abstract translation: 一种用于生成复合部件的计算机模型的方法包括：基于层叠区域和层叠曲面生成表面网格，并生成包括相对于层叠区域的多个节点的节点数据。 该方法还包括接收与多个复合层相关的复合数据，并且基于复合数据生成三维模型。 所述方法还包括基于所述铺垫表信息来接收叠加表信息和应用所述节点数据，以通过所述表面网格的中心生成曲线以限定多个元素集合。 该方法还包括接收复合覆盖数据，并且基于悬垂数据确定每个元素集合与三维模型相交的位置。 该方法还包括基于元件组的交点分析层的角度偏差。
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