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    Attachment of composite article
    2.
    发明授权
    Attachment of composite article 有权

    公开(公告)号：US09777579B2

    公开(公告)日：2017-10-03

    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 ,  F01D5/28 ,  F01D5/30

    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.

    ATTACHMENT OF COMPOSITE ARTICLE
    4.
    发明申请
    ATTACHMENT OF COMPOSITE ARTICLE 有权
    复合材料附件

    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。

    COMPOSITE BLADE WITH UNI-TAPE AIRFOIL SPARS
    5.
    发明申请
    COMPOSITE BLADE WITH UNI-TAPE AIRFOIL SPARS 审中-公开
    复合叶片与独特的飞机空间

    公开(公告)号：US20140112796A1

    公开(公告)日：2014-04-24

    申请号：US13658209

    申请日：2012-10-23

    Applicant: General Electric Company

    Inventor： Nicholas Joseph Kray ,  Ian Francis Prentice ,  Tod Winton Davis ,  Dong-Jin Shim ,  Pranav Dhoj Shah

    IPC: F01D5/28

    CPC classification number: F01D5/282 ,  F01D5/147 ,  F01D5/16 ,  F04D29/023 ,  F04D29/324 ,  F05D2220/36 ,  F05D2240/305 ,  F05D2240/306 ,  F05D2260/941 ,  F05D2300/603 ,  F05D2300/6034 ,  Y02T50/672

    Abstract: A gas turbine engine composite blade includes an airfoil having pressure and suction sides extending outwardly in a spanwise direction from a blade root along a span to a blade tip. A core section of the blade including composite quasi-isotropic plies extends spanwise outwardly through the blade. One or more spars including a stack of uni-tape plies having predominately a 0 degree fiber orientation with respect to the span and extending spanwise outwardly through the root and a portion of the airfoil towards the tip. Spars may include pressure and suction side spars sandwiching a chordwise extending portion of the core section in the airfoil and which be located near or along the pressure and suction sides respectively. Chordwise extending portion may be centered about a maximum thickness location of the airfoil. Spars may have height, width, and thickness that avoids flexural airfoil modes.

    Abstract translation: 燃气涡轮发动机复合叶片包括具有压力和吸力侧的翼型件，翼面方向上的叶片根部沿着跨度向叶片顶端向外延伸。 包括复合准各向同性层的叶片的核心部分通过叶片向外延伸。 一个或多个翼梁，其包括相对于跨距具有主要为0度纤维取向的单层帘布层的堆叠，并且沿翼部向外延伸穿过根部，并且一部分翼型朝向尖端。 翼梁可以包括压力和吸力侧翼片，其将翼部的芯部的弦向延伸部分夹在翼型中，并且分别位于压力侧和吸力侧附近或沿其。 弦翼延伸部分可以围绕翼型件的最大厚度位置居中。 翼梁可能具有避免弯曲翼型的高度，宽度和厚度。

    Braided blades and vanes having dovetail roots
    8.
    发明授权
    Braided blades and vanes having dovetail roots 有权

    公开(公告)号：US10589475B2

    公开(公告)日：2020-03-17

    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: F01D5/14 ,  B29C70/24 ,  F01D9/04 ,  F01D25/00 ,  F01D5/28 ,  B29C70/44 ,  B29C70/48

    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.

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