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    AIRFOIL SINGLETS
    12.
    发明申请
    AIRFOIL SINGLETS 审中-公开

    公开(公告)号：US20180080478A1

    公开(公告)日：2018-03-22

    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

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

    CPC classification number: F04D29/644 ,  F01D9/042 ,  F04D29/023 ,  F04D29/542 ,  F05D2240/80 ,  F05D2260/31 ,  F05D2300/6033 ,  F05D2300/6034 ,  Y02T50/672

    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.

    COMPOSITE BLADE WITH UNI-TAPE AIRFOIL SPARS
    14.
    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。

    Relative position measurement
    18.
    发明授权
    Relative position measurement 有权

    公开(公告)号：US11156119B2

    公开(公告)日：2021-10-26

    申请号：US16564433

    申请日：2019-09-09

    Applicant: General Electric Company

    Inventor： Ian Francis Prentice

    IPC: F01D17/12 ,  F01D17/02 ,  F04D27/00 ,  F04D29/32 ,  G01B7/30 ,  G01D5/20

    Abstract: A feedback sensor system is provided. The feedback sensor system includes a first ring rotatable about an axial direction and a second ring also rotatable about the axial direction. The first ring includes one or more first ring features and the second ring includes one or more second ring features. The feedback sensor system also includes a sensor directed at the surface of the first ring for sensing a parameter influenced by the one or more first ring features and the one or more second ring features. The sensor may determine a position of the first ring relative to the second ring by sensing the parameter.

    Braided blades and vanes having dovetail roots
    20.
    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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