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公开(公告)号：US20190153995A1
公开(公告)日：2019-05-23
申请号：US15818980
申请日：2017-11-21
Applicant: General Electric Company
Inventor： James Robert Tobin , Thomas Merzhaeuser , Peggy Lynn Baehmann
Abstract: A method for manufacturing an outer skin of a rotor blade includes forming an outer skin layer of the outer skin from a first combination of at least one of one or more resins or fiber materials. The method also includes forming an inner skin layer of the outer skin from a second combination of at least one of one or more resins or fiber materials. More specifically, the first and second combinations are different. Further, the method includes arranging the outer and inner skin layers together in a stacked configuration. In addition, the method includes joining the outer and inner skin layers together to form the outer skin.
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公开(公告)号：US20160311519A1
公开(公告)日：2016-10-27
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
IPC: B64C7/00
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.
Abstract translation: 放置在风力涡轮机轮毂前方的空气动力学圆顶部件包括外圈，相对于外圈设置的中心轴，多个径向延伸的张紧构件和皮肤状覆盖物。 多个径向延伸的张紧构件在第二端处连接到外环并且在第二端处联接到中心轴。 外环，多个径向延伸的张紧构件和中心轴一起形成下面的圆顶支撑结构。 皮肤状的覆盖物构造成包围下面的圆顶支撑结构的至少一部分以形成空气动力学圆顶部件的至少一部分并且限定一个前圆顶部分。 覆盖下面的圆顶支撑结构的至少一部分的皮肤状的覆盖物还可以限定后部圆顶部分，其中后部圆顶部分从前部圆顶部分构造成顺风向。
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13.发明授权Composite article including composite to metal interlock and method of fabrication 有权复合材料包括复合金属互锁和制造方法公开(公告)号：US09040138B2
公开(公告)日：2015-05-26
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
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：US20140241895A1
公开(公告)日：2014-08-28
申请号：US13778646
申请日：2013-02-27
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Chandra Sekher Yerramalli , Peggy Lynn Baehmann , Ken Ivcar Salas , Mohammad Salah Attia , Haifeng Zhao
IPC: F01D5/14
CPC classification number: F03D1/0675 , F03D1/0683 , F05D2230/23 , Y02E10/721 , Y10T29/49336
Abstract: A fluid turbine blade and method of fabrication are provided. The fluid turbine blade includes a centrally disposed longitudinal spar having a substantially circumferential cross section. The fluid turbine blade also includes at least one chord stiffener coupled to the longitudinal spar. The fluid turbine blade further includes a torsionally compliant segmented skin coupled to the at least one chord stiffener. The centrally disposed longitudinal spar and the torsionally compliant segmented skin are functionally decoupled to relieve the torsionally compliant segmented skin of one or more of a flapwise load condition, an edgewise load condition and a torsional load condition.
Abstract translation: 提供了一种流体涡轮叶片及其制造方法。 流体涡轮机叶片包括具有基本上圆周的横截面的居中设置的纵向翼梁。 流体涡轮机叶片还包括耦合到纵向翼梁的至少一个弦加强筋。 流体涡轮叶片还包括耦合到至少一个弦加劲肋的扭转顺应的分段皮肤。 中心设置的纵向翼梁和扭转顺应性分段的皮肤在功能上解耦，以减轻扭转顺应的分段皮肤，其中一个或多个翼板载荷状态，沿边载荷状态和扭转载荷状态。
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15.发明申请公开(公告)号：US20190153994A1
公开(公告)日：2019-05-23
申请号：US15818957
申请日：2017-11-21
Applicant: General Electric Company
Inventor： James Robert Tobin , Norman Arnold Turnquist , Stephen Bertram Johnson , Don Conrad Johnson , Thomas Merzhaeuser , Peggy Lynn Baehmann , Stefan Herr , Murray Fisher , Andrew McCalip , Alan M. Walker , Todd Anderson
Abstract: A method for manufacturing a rotor blade panel of a wind turbine includes placing one or more fiber-reinforced outer skins into a mold of the rotor blade panel. The method also includes printing and depositing, via a computer numeric control (CNC) device, a plurality of rib members that form at least one three-dimensional (3-D) reinforcement grid structure onto an inner surface of the one or more fiber-reinforced outer skins. Further, the grid structure bonds to the one or more fiber-reinforced outer skins as the grid structure is deposited. Moreover, the method includes printing at least one additional feature into the grid structure.
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Patent Agency Ranking
公开(公告)号：US20180105245A1
公开(公告)日：2018-04-19
申请号：US15295601
申请日：2016-10-17
Applicant: General Electric Company
IPC: B63H1/20
Abstract: An apparatus and system for a marine propeller assembly are provided. An aft retention member that may be used with the marine propeller assembly includes a base, an opposing nose and a conic body extending therebetween along a centerline normal to the base. The aft retention member also includes at least one protuberance extending radially away from a surface of the conic body. The protuberance extends axially along a surface of the aft retention member from the base arcuately convergent to a predetermined point between the base and a tip of the nose.
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公开(公告)号：US20180105242A1
公开(公告)日：2018-04-19
申请号：US15295303
申请日：2016-10-17
Applicant: General Electric Company
IPC: B63H1/20
CPC classification number: B63H1/20 , B63H1/28 , B63H2001/283 , F01D11/008
Abstract: A propeller assembly is provided. The propeller assembly includes a central hub including a forward end, an aft end, and a hub body extending therebetween along an axis of rotation of the central hub. The propeller assembly further includes a first retention member including a first radial interference member, the first retention member coupled to the forward end of the central hub and a second retention member including a second radial interference member, the second retention member coupled to the aft end of the central hub. The propeller assembly also includes a fairing platform extending between the first retention member and the second retention member, wherein the fairing platform is retained by the first radial interference member and by the second radial interference member.
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公开(公告)号：US20180105241A1
公开(公告)日：2018-04-19
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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19.发明申请公开(公告)号：US20170145986A1
公开(公告)日：2017-05-25
申请号：US14952767
申请日：2015-11-25
Applicant: General Electric Company
Inventor： Peggy Lynn Baehmann , Shridhar Champaknath Nath , Shatil Sinha
CPC classification number: F03D1/0675 , B29D99/0028 , B29L2031/085 , B33Y10/00 , B33Y50/00 , B33Y80/00 , F05B2230/31 , F05B2230/50 , F05B2240/302 , F05B2280/6003 , Y02E10/721 , Y02P70/523
Abstract: A rotor blade assembly including a first blade section including a joint end and a custom fit second blade section including a joint end, and a method of fabricating the rotor blade assembly is disclosed. One of the first blade section or the custom fit second blade section includes an inner surface defining a cavity. The cavity is configured to receive the joint end of the other one of the blade sections in an overlapping configuration to define an overlapping region and a mating joint. A joining means is used to secure the joint ends of the blade sections. A profile of the outer surface of the custom fit second blade section generally corresponds to the aerodynamic profile of the first blade section such that a substantially continuous aerodynamic profile is defined between the blade sections when the joint ends are configured in the overlapping configuration.
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20.发明授权Fluid turbine blade with torsionally compliant skin and method of providing the same 有权具有扭曲兼容皮肤的流体涡轮叶片及其提供方法公开(公告)号：US09534580B2
公开(公告)日：2017-01-03
申请号：US13778646
申请日：2013-02-27
Applicant: General Electric Company
Inventor： Chandra Sekher Yerramalli , Peggy Lynn Baehmann , Ken Ivcar Salas , Mohammad Salah Attia , Haifeng Zhao
IPC: F03D1/06
CPC classification number: F03D1/0675 , F03D1/0683 , F05D2230/23 , Y02E10/721 , Y10T29/49336
Abstract: A fluid turbine blade and method of fabrication are provided. The fluid turbine blade includes a centrally disposed longitudinal spar having a substantially circumferential cross section. The fluid turbine blade also includes at least one chord stiffener coupled to the longitudinal spar. The fluid turbine blade further includes a torsionally compliant segmented skin coupled to the at least one chord stiffener. The centrally disposed longitudinal spar and the torsionally compliant segmented skin are functionally decoupled to relieve the torsionally compliant segmented skin of one or more of a flapwise load condition, an edgewise load condition and a torsional load condition.
Abstract translation: 提供了一种流体涡轮叶片及其制造方法。 流体涡轮机叶片包括具有基本上圆周的横截面的居中设置的纵向翼梁。 流体涡轮机叶片还包括耦合到纵向翼梁的至少一个弦加强筋。 流体涡轮叶片还包括耦合到至少一个弦加劲肋的扭转顺应的分段皮肤。 中心设置的纵向翼梁和扭转顺应性分段的皮肤在功能上解耦，以减轻扭转顺应的分段皮肤，其中一个或多个翼板载荷状态，沿边载荷状态和扭转载荷状态。
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