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    Hybrid Composite Components
    1.
    发明公开
    Hybrid Composite Components 审中-公开

    公开(公告)号：US20240076997A1

    公开(公告)日：2024-03-07

    申请号：US18330841

    申请日：2023-06-07

    Applicant: General Electric Company

    Inventor： Nicholas Joseph KRAY ,  Nitesh JAIN

    IPC: F01D21/04 ,  F01D25/24

    CPC classification number: F01D21/045 ,  F01D25/24 ,  F02K3/06 ,  F05D2220/36 ,  F05D2240/14

    Abstract: Hybrid composite components, such as gas turbine engine containment assemblies, a hybrid composite component having an annular composite shell and an annular metallic shell joined with the composite shell. A containment assembly including a containment case extending along an axial direction about a longitudinal centerline of the gas turbine engine. The containment case has an inner surface and an outer surface spaced apart along a radial direction and includes a first composite shell joined with a metallic shell. The metallic shell defining a first portion of the inner surface and the first composite shell defining a second portion of the inner surface.

    FIBER PLACEMENT MACHINE ROLLER WITH VACCUM ASSISTED TOW HANDLING
    2.
    发明申请
    FIBER PLACEMENT MACHINE ROLLER WITH VACCUM ASSISTED TOW HANDLING 有权

    公开(公告)号：US20170080646A1

    公开(公告)日：2017-03-23

    申请号：US14857858

    申请日：2015-09-18

    Applicant: General Electric Company

    Inventor： Mark Ernest VERMILYEA ,  Nicholas Joseph KRAY

    IPC: B29C70/38 ,  B29C70/54

    CPC classification number: B29C70/382 ,  B29C70/386 ,  B29C70/54

    Abstract: A fiber placement system is provided that can include a compaction roller defining a plurality of openings between a roller outer surface and a roller inner surface. The plurality of openings are in fluid communication with a vacuum source. A cover can be included in or on the compaction roller so as to block airflow through a portion of the openings. The fiber placement system can also include a head including a frame and at least one supply spool mounted on the frame. The supply spool is supported on a hub for rotation, and the compaction roller is aligned to receive one or more fiber tows from the at least one supply spool. Methods are also provided for laying a prepreg tow material using automated fiber placement.

    BRAIDED BLADES AND VANES HAVING DOVETAIL ROOTS
    6.
    发明申请
    BRAIDED BLADES AND VANES HAVING DOVETAIL ROOTS 审中-公开
    具有刀片的刀片和花边

    公开(公告)号：US20160201478A1

    公开(公告)日：2016-07-14

    申请号：US14860132

    申请日：2015-09-21

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Nicholas Joseph KRAY ,  Xiaomei FANG ,  Christopher MADSEN ,  Ian Francis PRENTICE ,  Sultan SHAIR ,  Dong-Jin SHIM ,  Douglas Duane WARD

    IPC: F01D5/28 ,  F01D9/04 ,  F01D25/00 ,  F01D5/14

    Abstract: A gas turbine engine composite article having a composite article airfoil extending outwardly to an article root to an article airfoil tip. Within the article airfoil is a core including a core airfoil attached to a core root including a core dovetail. A continuous outer three-dimensional braided layer including braided composite material tows are braided on the core and the braided layer covers the entire core airfoil and the core root. The core may be an inflatable mandrel or a composite core made of a composite material. The core may include stiffeners such as an I beam or hollow rectangular cross-section box beams. A method for making such an article includes braiding a continuous outer three-dimensional braided layer including braided composite material tows on the core including covering the entire core airfoil and the core root with the continuous outer three-dimensional braided layer.

    Abstract translation: 一种燃气涡轮发动机复合制品，其具有向外延伸到制品根部到制品翼型尖端的复合制品翼型件。 在该文件中，翼型件是一种核心，包括一个附着在核心根部上的核心翼型件，其中包括核心燕尾榫。 包括编织复合材料丝束的连续外部三维编织层编织在芯上，编织层覆盖整个核心翼型和芯根。 芯可以是可充气心轴或由复合材料制成的复合芯。 芯可以包括加强件，例如I梁或中空矩形横截面箱梁。 制造这种制品的方法包括在芯体上编织包括编织复合材料丝束的连续的外部三维编织层，包括用连续的外部三维编织层覆盖整个核心翼型和芯根。

    METHOD FOR MANUFACTURING LEADING EDGE GUARD
    7.
    发明申请
    METHOD FOR MANUFACTURING LEADING EDGE GUARD 审中-公开
    制造边缘护板的方法

    公开(公告)号：US20170044681A1

    公开(公告)日：2017-02-16

    申请号：US15304682

    申请日：2015-04-02

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Qiang LI ,  Nicholas Joseph KRAY ,  Michael W. PERETTI ,  Tod Winton DAVIS

    IPC: C25D1/02 ,  F04D29/38 ,  F04D29/32

    CPC classification number: C25D1/02 ,  C25D1/00 ,  F04D29/325 ,  F04D29/388

    Abstract: A method for making a metallic leading edge guard of the type haying a nose with first and second wings extending therefrom is disclosed. The method includes machining from a metallic blank a first half comprising a first portion of the nose and one of the wings, wherein the first portion of the nose includes an interface surface; and electroforming a second half comprising a second portion of the nose and the second wing, wherein the second half is joined to the first half at the interface surface.

    Abstract translation: 公开了一种用于制造具有从其延伸的第一和第二翼的鼻子类型的金属前缘防护件的方法。 该方法包括从金属坯料加工包括鼻部的第一部分和翼中的一个的第一半部，其中鼻部的第一部分包括界面; 以及电铸第二半部分，其包括所述鼻部和所述第二机翼的第二部分，其中所述第二半部在所述界面处接合到所述第一半部。

    COMPOSITE DISK
    8.
    发明申请
    COMPOSITE DISK 有权
    复合盘

    公开(公告)号：US20160362990A1

    公开(公告)日：2016-12-15

    申请号：US14734091

    申请日：2015-06-09

    Applicant: General Electric Company

    Inventor： Nicholas Joseph KRAY ,  Baskaran BHUVARAGHAN ,  Nitesh JAIN

    IPC: F01D5/30

    CPC classification number: F01D5/3023 ,  B29C70/345 ,  B29C70/48 ,  B29D99/0025 ,  F01D5/028 ,  F01D5/282 ,  F01D5/3007 ,  F05D2220/36

    Abstract: A gas turbine engine composite disk includes dovetail slots between disk posts extending radially inwardly from a periphery, a hub ring of composite plies circumscribed about a centerline axis, and radial plies extending radially away from hub ring into disk posts. A segmented intermediate ring concentric with and located radially outwardly of hub ring includes intermediate ring segments having nested plies with annular bases circumscribed about centerline axis and substantially radially extending clockwise and counter-clockwise radial ply arms. An outer segmented ring may be concentric with and located radially outwardly of intermediate ring, include annular outer ring segments with circumferentially stacked composite plies disposed within intermediate ring segments between clockwise and counter-clockwise radial ply arms and radially outwardly of annular bases. An outer skin of outermost composite covering plies may extend circumferentially around composite disk. Circumferential and radial composite plies may include circumferentially and radially oriented fibers.

    Abstract translation: 燃气涡轮发动机复合盘包括在从周边径向向内延伸的盘柱之间的燕尾槽，围绕中心线轴线包围的复合帘布层的轮毂圈，以及从轮毂环径向延伸到盘柱的径向帘布层。 与轮毂环径向向外同心并且位于毂环径向向外的分段中间环包括具有嵌套层的中间环段，环状基部围绕中心线轴线以及基本径向延伸的顺时针和逆时针径向层叠臂。 外部分段环可以与中间环同心并位于中间环的径向向外，包括环形外环段，其具有周向堆叠的复合层，设置在顺时针和逆时针径向层叠臂之间的中间环段内，并且环形基底的径向向外。 最外面的复合材料覆盖层的外皮可围绕复合盘周向延伸。 周向和径向复合层可以包括周向和径向取向的纤维。

    COMPOSITE AIRFOIL METAL LEADING EDGE ASSEMBLY
    10.
    发明申请
    COMPOSITE AIRFOIL METAL LEADING EDGE ASSEMBLY 审中-公开
    复合气垫金属导线边缘组件

    公开(公告)号：US20160010468A1

    公开(公告)日：2016-01-14

    申请号：US14771970

    申请日：2013-03-01

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Nicholas Joseph KRAY ,  Qiang LI ,  Richard W. ALBRECHT, JR.

    IPC: F01D5/28 ,  F01D5/14 ,  F01D9/04

    CPC classification number: F01D5/28 ,  B23P15/04 ,  F01D5/147 ,  F01D5/282 ,  F01D5/288 ,  F01D9/041 ,  F04D29/324 ,  F05D2220/32 ,  F05D2230/23 ,  F05D2230/60 ,  F05D2240/303 ,  F05D2300/133 ,  F05D2300/171 ,  F05D2300/174 ,  Y02T50/672

    Abstract: An airfoil assembly (30) comprises a composite airfoil (40) having a leading edge (32) and a trailing edge (34), a pressure side (36) extending between the leading edge and the trailing edge, a suction side (38) extending between the leading edge and the trailing edge, opposite the leading edge, a metallic leading edge assembly (130) disposed over the composite air-foil, the metallic leading edge assembly including a high density base (50), the metallic leading edge assembly also including a nose (60) disposed over the base, an adhesive bond layer disposed between the composite airfoil and the metallic leading edge assembly.

    Abstract translation: 翼型组件（30）包括具有前缘（32）和后缘（34）的复合翼型件（40），在前缘和后缘之间延伸的压力侧（36），吸力侧（38） 在所述前缘和所述后缘之间延伸，与所述前缘相对，设置在所述复合空气箔上方的金属前缘组件，所述金属前缘组件包括高密度基座（50），所述金属前缘组件 还包括设置在所述基座上方的鼻部（60），设置在所述复合翼面和所述金属前缘组件之间的粘合剂粘结层。

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