中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

286 records (took 0.075 seconds)

    COMPOSITE ARTICLE INCLUDING COMPOSITE TO METAL INTERLOCK AND METHOD OF FABRICATION
    162.
    发明申请
    COMPOSITE ARTICLE INCLUDING COMPOSITE TO METAL INTERLOCK AND METHOD OF FABRICATION 有权
    复合材料包括复合材料到金属互连和制造方法

    公开(公告)号：US20140322482A1

    公开(公告)日：2014-10-30

    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

    IPC: B32B7/08

    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。

    SPINNER ASSEMBLY WITH REMOVABLE FAN BLADE LEADING EDGE FAIRINGS
    163.
    发明申请
    SPINNER ASSEMBLY WITH REMOVABLE FAN BLADE LEADING EDGE FAIRINGS 有权
    旋转器组件与可拆卸的风扇叶片领先的边缘公平

    公开(公告)号：US20140212295A1

    公开(公告)日：2014-07-31

    申请号：US13755426

    申请日：2013-01-31

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Nicholas Joseph Kray ,  Jorge Orlando Lamboy

    IPC: F01D5/02

    CPC classification number: F01D5/02 ,  F02C7/04 ,  F05D2300/43 ,  Y02T50/671

    Abstract: A gas turbine engine spinner assembly including a spinner defining at least in part an aerodynamically smooth surface, a shell defining at least in part the aerodynamically smooth surface, and circumferentially spaced apart removable aerodynamic fairings located around the shell. Fairing shanks disposed in circumferentially spaced apart axially extending slots in the shell may be attached to the aerodynamic fairings. The fairings may shield radially extending portions of the fan blades including portions of blade shanks or portions of transition regions of the blade shanks. The fairing shanks may be disposed between and monolithically formed with the fairings and fairing roots attached to the fairing shanks. The fairings may be made of an injectable thermoplastic and the shell made of metal. The fairing shanks may be setback from fairing forward tips and the fairing shanks may be setback from root forward tips of the fairing roots.

    Abstract translation: 一种燃气涡轮发动机旋转器组件，其包括至少部分地限定空气动力学平滑表面的旋转器，至少部分地限定空气动力学平滑表面的壳体，以及围绕壳体的周向间隔开的可移除空气动力学整流罩。 布置在外壳中沿周向间隔开的轴向延伸的狭槽的整流罩可附接到空气动力学整流罩。 整流罩可以屏蔽风扇叶片的径向延伸部分，包括叶片柄的部分或叶片柄的过渡区域的部分。 整流罩可以布置在整流罩和整流罩之间，整流罩和整流罩根部连接在整流罩上。 整流罩可由可注射的热塑性材料制成，外壳由金属制成。 整流罩可能会从整流罩前端引起挫折，整流罩可能会从整流罩根部的根尖向后倾斜。

    COMPOSITE BLADE WITH UNI-TAPE AIRFOIL SPARS
    164.
    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。

    TURBINE ENGINE WITH COMPLIANT AXIAL RETAINER
    165.
    发明申请
    TURBINE ENGINE WITH COMPLIANT AXIAL RETAINER 有权

    公开(公告)号：US20250109690A1

    公开(公告)日：2025-04-03

    申请号：US18480169

    申请日：2023-10-03

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Nicholas Joseph Kray ,  Elzbieta Kryj-Kos ,  Arthur William Sibbach

    IPC: F01D5/14 ,  F01D5/28

    Abstract: A gas turbine engine includes a fan section, a compressor section, a combustion section, and a turbine section in serial flow arrangement, and defining an engine centerline extending between a forward direction and an aft direction. A disk includes a slot for mounting a composite airfoil to the disk. An axial retainer couples to the disk and secures the composite airfoil to the disk. A compliant portion positioned at the composite airfoil abuts the composite airfoil during operation of the gas turbine engine to secure the composite airfoil to the disk.

    TURBINE ENGINE WITH COMPOSITE AIRFOILS
    170.
    发明申请
    TURBINE ENGINE WITH COMPOSITE AIRFOILS 有权

    公开(公告)号：US20240401488A1

    公开(公告)日：2024-12-05

    申请号：US18806835

    申请日：2024-08-16

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Nicholas Joseph Kray ,  Arthur William Sibbach

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

    Abstract: A turbine engine with an engine core defining an engine centerline and comprising a rotor and a stator. The turbine engine including a set of composite airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.

Patent Agency Ranking