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    Composite article and methods therefor
    2.
    发明授权
    Composite article and methods therefor 审中-公开

    公开(公告)号：US10654246B2

    公开(公告)日：2020-05-19

    申请号：US13687117

    申请日：2012-11-28

    Applicant: General Electric Company

    Inventor： Ming Xie ,  Mark Ernest Vermilyea ,  Bowden Kirkpatrick ,  Mitchell Harold Boyer ,  Elliott Keller Schulte ,  Benjamin Ferrell

    IPC: B32B5/12 ,  F01D25/24 ,  B32B37/14 ,  B29C70/30

    Abstract: A method is provided for forming a composite article to have a primary composite structure and an integral secondary composite structure that extends out of a plane defined by the primary composite structure. The method includes laying-up first plies to construct the primary composite structure. The first plies contain continuous reinforcement material and extend from a first zone that will define the primary composite structure into a second zone that will define the secondary composite structure. During laying-up of the first plies, additional plies are interleaved with the first plies within the second zone but not the first zone. The additional plies originate within a build-up zone between the first and second zones and extend therefrom into the second zone. After interleaving the plies, the build-up zone is deformed to orient the second zone and form the secondary composite structure that extends out of the plane defined by the continuous reinforcement material of the first plies.

    Airfoil singlets
    3.
    发明授权
    Airfoil singlets 有权

    公开(公告)号：US10443625B2

    公开(公告)日：2019-10-15

    申请号：US15271312

    申请日：2016-09-21

    Applicant: General Electric Company

    Inventor： Leslie Louis Langenbrunner ,  Ian Francis Prentice ,  Rosa Lee Nemec ,  Adam Max Aresty ,  Ming Xie ,  Andrew McGee

    IPC: F04D29/64 ,  F04D29/02 ,  F04D29/52 ,  F04D29/54 ,  F01D9/04

    Abstract: Composite airfoil singlet, includes airfoil extending from base to tip of airfoil, integrally formed with no more than one outer platform at tip and/or no more than one inner platform at base. Parallel composite plies or woven fibers extend through airfoil and through outer and/or inner platforms. Outer and/or inner curved sections extend between outer and/or inner platforms and airfoil respectively. Assembly includes circular row of the composite airfoil singlets depending radially inwardly from and mounted to an outer shroud or casing. Outer and/or inner fasteners may secure outer and inner platforms to outer shroud or casing and an inner shroud respectively and include shanks extending substantially perpendicularly from outer and inner fastening plates though platform holes in outer and inner platforms and through outer and inner holes in outer shroud or casing and inner shroud respectively. Nuts are screwed on threaded ends of shanks.

    Non-integral fan blade platform
    4.
    发明授权
    Non-integral fan blade platform 有权
    非整体风扇叶片平台

    公开(公告)号：US09399922B2

    公开(公告)日：2016-07-26

    申请号：US13731459

    申请日：2012-12-31

    Applicant: General Electric Company

    Inventor： Jorge Orlando Lamboy ,  Matthew Glen Gann ,  Nicholas Joseph Kray ,  Gerald Alexander Pauley ,  Daniel Allen Wilkin, II ,  Ming Xie

    IPC: F01D5/30 ,  F01D11/00 ,  F02K3/06 ,  F04D29/32 ,  F04D29/64

    CPC classification number: F01D5/3038 ,  F01D5/3007 ,  F01D11/008 ,  F02K3/06 ,  F04D29/321 ,  F04D29/644 ,  F05D2220/36 ,  F05D2260/30 ,  Y02T50/672 ,  Y10T29/4932

    Abstract: Described are a gas turbine engine fan blade platform, related rotor assembly and gas turbine engine, as well as a method of assembling the same. The platform has a forward portion proximal to an axis of rotation, an aft portion, and a transition portion between the forward and aft portions. The forward portion has a forward interface surface facing axially forward, the aft portion has an aft interface surface facing radially outward, and the transition portion has at least one mounting feature. For the method of assembly, an aft support is installed on a fan disk and booster spool assembly. A plurality of fan blades are installed into a fan disk, followed by installing a fan platform between adjacent blades and securing the mounting features to the disk, thereby filling the annulus of the fan disk. Finally, a forward support is installed on the fan disk.

    Abstract translation: 描述了一种燃气涡轮发动机风扇叶片平台，相关的转子组件和燃气涡轮发动机，以及其组装方法。 平台具有靠近旋转轴线的前部，后部部分和前部和后部之间的过渡部分。 前部具有面向轴向前方的前向接口表面，后部具有面向径向外侧的后界面，并且该过渡部具有至少一个安装特征。 对于组装方法，后部支撑件安装在风扇盘和助力阀芯组件上。 将多个风扇叶片安装到风扇盘中，随后在相邻叶片之间安装风扇平台并将安装特征固定到盘上，从而填充风扇盘的环形空间。 最后，风扇盘上安装了前向支持。

    METHOD AND SYSTEM FOR FIBER REINFORCED COMPOSITE PANELS
    7.
    发明申请
    METHOD AND SYSTEM FOR FIBER REINFORCED COMPOSITE PANELS 审中-公开

    公开(公告)号：US20170204870A1

    公开(公告)日：2017-07-20

    申请号：US14996626

    申请日：2016-01-15

    Applicant: General Electric Company

    Inventor： Ming Xie

    IPC: F04D29/02 ,  F04D29/52

    CPC classification number: F04D29/023 ,  F01D21/045 ,  F04D29/526 ,  F05D2220/36 ,  F05D2230/50 ,  F05D2240/14 ,  F05D2240/30 ,  F05D2250/283 ,  F05D2300/603 ,  F05D2300/6034 ,  F05D2300/614 ,  Y02T50/672

    Abstract: A composite panel structure and a method of fabricating the composite panel structure are provided. A fan assembly includes a plurality of blades circumferentially spaced about a fan disk. Each blade of the plurality of blades extends radially outwardly from the disk to a blade tip. A fan case assembly circumscribes the plurality of blades. The fan case assembly includes a radially outer casing including a radially inner side, an inner structure including an inner surface and a honeycomb layer extending along the radially inner side, and a composite panel structure including an inner surface and extending circumferentially along the inner structure inner surface. The composite panel structure includes short fiber tows extending only partially along at least one of a circumferential path, an axial path, and a diagonal path in the composite panel structure.

    Fiber preform architecture for composite articles and method of fabrication
    8.
    发明授权
    Fiber preform architecture for composite articles and method of fabrication 有权
    用于复合制品的纤维预制架构和制造方法

    公开(公告)号：US09249530B2

    公开(公告)日：2016-02-02

    申请号：US13906127

    申请日：2013-05-30

    Applicant: General Electric Company

    Inventor： Yosang Yoon ,  Mark Ernest Vermilyea ,  Teresa Tiashu Chen-Keat ,  Ming Xie

    IPC: D03D1/00 ,  B29B11/16 ,  B29C70/22 ,  B29C70/30 ,  B29C53/58 ,  B29C53/60 ,  B29L31/00

    CPC classification number: D03D1/00 ,  B29B11/16 ,  B29C53/582 ,  B29C53/60 ,  B29C70/222 ,  B29C70/30 ,  B29L2031/7504

    Abstract: A fiber preform architecture and method of making, including a plurality of fiber bands. Each band of the plurality of fiber bands is placed at a time, at a predetermined position and orientation, to generate an interwoven and interlocking pattern between the fiber bands. Each of the plurality of fiber bands is formed of a plurality of fiber tows, positioned side by side at a predetermined spacing to define one or more gaps between each tow in the fiber band and define a secondary based interleaving within each of the fiber bands. 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 with one or more of the plurality of fiber bands previously laid down and not in a common plane. The plurality of fiber bands include three or more different orientation angles and provide uniformity in coverage.

    Abstract translation: 纤维预制体结构和制造方法，包括多个纤维带。 多个光纤带中的每个带都被放置在一个预定的位置和方位的时间，以在光纤带之间产生交织和互锁图案。 多个光纤带中的每一个由多个纤维束形成，以预定的间隔并排放置，以在光纤带中的每个丝束之间限定一个或多个间隙，并在每个光纤带内限定二次基交织。 多个光纤带通过将多个光纤带中的每个纤维带与先前放置的多个光纤带中的一个或多个而不是在共同的平面交错而以平面内和面外取向交织。 多个光纤带包括三个或更多个不同的取向角并提供覆盖的均匀性。

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