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公开(公告)号：US11052982B2
公开(公告)日：2021-07-06
申请号：US15295168
申请日：2016-10-17
Applicant: General Electric Company
Abstract: A blade member includes a leading edge, a trailing edge, and a blade body extending therebetween. The blade member also includes a dovetail, a transition region, and a transition relief. The dovetail includes a dovetail chord line extending between an axially forward face of the dovetail and an axially aft face of the dovetail. The dovetail chord line has a dovetail chord length. The transition region is formed between the blade body and the dovetail. The blade body and the transition region form a blade body transition chord line at the interface of the blade body and the transition region which has a blade body transition chord length. The transition relief includes a geometric relief in at least one of a forward and an aft end of the transition region and the dovetail. The dovetail chord length is less than the blade body transition chord length.
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公开(公告)号：US10132290B2
公开(公告)日：2018-11-20
申请号：US14887381
申请日：2015-10-20
Applicant: General Electric Company
Inventor： Dmitry Floryovych Opaits , Seyed Gholamali Saddoughi , Grover Andrew Bennett , Matthew Patrick Boespflug , Stephen Bertram Johnson , Peggy Lynn Baehmann , Fulton Jose Lopez , Daniel Jason Erno , Robert Michael Zirin , Anurag Gupta
IPC: F03D1/06
Abstract: A deployable aerodynamic component configured to be mounted to a wind turbine. The wind turbine includes at least one rotor blade. The deployable aerodynamic component configured to be positioned in front of an inner portion of the at least one rotor blade, and is structurally configured to cover a substantial portion of the inner portion of the at least one rotor blade in a wind direction during deployment of the deployable aerodynamic component and to allow the passage therethrough of an incoming wind when non-deployed. Further described is a wind turbine including the above-described deployable aerodynamic component and method for aerodynamic performance enhancement of an existing wind turbine, wherein the method includes mounting the above-described deployable aerodynamic component to a wind turbine.
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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：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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公开(公告)号：US20150233342A1
公开(公告)日：2015-08-20
申请号：US14183892
申请日：2014-02-19
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Peggy Lynn Baehmann , Fulton Jose Lopez , Ian David Wilson , Robert Michael Zirin
IPC: F03D1/04
CPC classification number: F03D1/04 , F03D1/0691 , F05B2240/14 , Y02E10/721 , Y02E10/726 , Y10T29/49316
Abstract: An aerodynamic dome structure that is placed in front of a wind turbine hub includes a plurality of arcuate panels. The arcuate panels are interconnected to form a dome-shaped structure. A plurality of arcuate radial spar supports may be employed to support the arcuate panels.
Abstract translation: 放置在风力涡轮机轮毂前方的空气动力学圆顶结构包括多个弧形面板。 弓形面板相互连接形成圆顶形结构。 可以采用多个弓形径向翼梁支撑件来支撑弓形面板。
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Patent Agency Ranking
公开(公告)号：US10507902B2
公开(公告)日：2019-12-17
申请号：US14692266
申请日：2015-04-21
Applicant: General Electric Company
Inventor： Fulton Jose Lopez , Daniel Jason Erno , Peggy Lynn Baehmann , Robert Michael Zirin
Abstract: An aerodynamic dome component that is placed in front of a wind turbine hub includes an outer ring, a central axle disposed relative to the outer ring, a plurality of radially extending tensioning members and a skin-like covering. The plurality of radially extending tensioning members are coupled to the outer ring at a first end and to the central axle at a second end. The outer ring, the plurality of radially extending tensioning members and the central axle together form an underlying dome support structure. The skin-like covering is configured to envelop at least a portion of the underlying dome support structure to form at least a portion of the aerodynamic dome component and define a front dome portion. The skin-like covering enveloping at least a portion of the underlying dome support structure may further define a rear dome portion, wherein the rear dome portion is configured downwind from the front dome portion.
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公开(公告)号：US09682756B1
公开(公告)日：2017-06-20
申请号：US15295259
申请日：2016-10-17
Applicant: General Electric Company
CPC classification number: B63H1/20 , B63B2748/00 , F01D5/30 , F05D2260/941 , Y02T50/672
Abstract: A propeller assembly includes a central hub including a first forward-facing end, a second aft-facing end, a hub body extending therebetween, and a plurality of channels spaced circumferentially around the central hub. The propeller assembly further includes blade wedges configured to be inserted into and to retain blades within the channels of the central hub. Each blade includes a blade dovetail including a dovetail face configured to engage a respective channel sidewall and/or a respective wedge sidewall. The dovetail face includes a bearing portion that engages the respective channel sidewall and/or the respective wedge sidewall and a clearance portion that is spaced from the respective channel sidewall and/or the respective wedge sidewall by a clearance gap during a first loading of the propeller assembly and that engages the respective channel sidewall or wedge sidewall during a second loading, the second loading greater than the first loading.
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8.发明申请APPARATUS AND METHOD FOR AERODYNAMIC PERFORMANCE ENHANCEMENT OF A WIND TURBINE 审中-公开风力涡轮机气动性能提升装置及方法公开(公告)号：US20160040650A1
公开(公告)日：2016-02-11
申请号：US14887381
申请日：2015-10-20
Applicant: General Electric Company
Inventor： Dmitry Floryovych Opaits , Seyed Gholamali Saddoughi , Grover Andrew Bennett , Matthew Patrick Boespflug , Stephen Bertram Johnson , Peggy Lynn Baehmann , Fulton Jose Lopez , Daniel Jason Erno , Robert Michael Zirin , Anurag Gupta
CPC classification number: F03D1/0625 , F03D1/0691 , F05B2240/12 , Y02E10/721 , Y10T29/49316
Abstract: A deployable aerodynamic component configured to be mounted to a wind turbine. The wind turbine includes at least one rotor blade. The deployable aerodynamic component configured to be positioned in front of an inner portion of the at least one rotor blade, and is structurally configured to cover a substantial portion of the inner portion of the at least one rotor blade in a wind direction during deployment of the deployable aerodynamic component and to allow the passage therethrough of an incoming wind when non-deployed. Further described is a wind turbine including the above-described deployable aerodynamic component and method for aerodynamic performance enhancement of an existing wind turbine, wherein the method includes mounting the above-described deployable aerodynamic component to a wind turbine.
Abstract translation: 配置为安装到风力涡轮机的可部署的空气动力学部件。 风力涡轮机包括至少一个转子叶片。 所述可部署空气动力学部件被构造成定位在所述至少一个转子叶片的内部部分的前面，并且在结构上构造成在所述至少一个转子叶片的展开期间在风向方向上覆盖所述至少一个转子叶片的内部部分的大部分 可部署的空气动力学部件，并且当未部署时允许通过其中的风。 进一步描述了一种风力涡轮机，其包括上述可部署的空气动力学部件和用于现有风力涡轮机的空气动力学性能增强的方法，其中所述方法包括将上述可部署空气动力学部件安装到风力涡轮机。
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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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公开(公告)号：US10689073B2
公开(公告)日：2020-06-23
申请号：US15295679
申请日：2016-10-17
Applicant: General Electric Company
Abstract: An apparatus and system for a marine propeller assembly are provided. In one aspect, the marine propeller assembly includes a plurality of circumferentially-spaced blades that each include a dovetail having a radial 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 radial inner surface and at least a portion of the dovetail receiving portion.
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