中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

292 records (took 0.024 seconds)

    Attachment of composite article
    52.
    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.

    Non-integral fan blade platform
    54.
    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。

    Spinner assembly with removable fan blade leading edge fairings
    55.
    发明授权
    Spinner assembly with removable fan blade leading edge fairings 有权
    带可拆卸风扇叶片前缘整流罩的旋转组件

    公开(公告)号：US09297257B2

    公开(公告)日：2016-03-29

    申请号：US13755426

    申请日：2013-01-31

    Applicant: General Electric Company

    Inventor： Nicholas Joseph Kray ,  Jorge Orlando Lamboy

    IPC: F01D5/02 ,  F02C7/04

    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。

    ATTACHMENT OF COMPOSITE ARTICLE
    56.
    发明申请
    ATTACHMENT OF COMPOSITE ARTICLE 有权
    复合材料附件

    公开(公告)号：US20140161621A1

    公开(公告)日：2014-06-12

    申请号：US13709651

    申请日：2012-12-10

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Nicholas Joseph Kray ,  Scott Roger Finn ,  Peggy Lynn Baehmann ,  Joel Primmer White

    IPC: F01D5/14

    CPC classification number: F01D5/147 ,  B29C70/202 ,  B29C70/38 ,  B29D99/0025 ,  B29L2031/082 ,  F01D5/282 ,  Y02T50/672

    Abstract: A composite article including composite component mounted on a spar including a shank extending heightwise from below component base up into composite component. Tab at an upper end of shank substantially or fully embedded in the composite component and at least one ply surface pattern of the composite component contacting and generally conforming to at least one spar surface pattern on the tab.Spar surface pattern may include spaced apart spar surface protrusions with spar surface spaces therebetween and spar surface protrusions extending outwardly from spar and disposed between tows in ply surface pattern. Tows may be layed up in spar surface spaces. Spar surface pattern may include continuous or segmented spaced spar surface protrusions and spar surface spaces therebetween with tows in ply surface pattern disposed in spar surface spaces. The composite article may be a composite blade or vane including a composite airfoil.

    Abstract translation: 一种复合制品，其包括安装在翼梁上的复合部件，该翼梁包括从下部部件基部向上高度延伸的复合部件。 基部或完全嵌入复合部件中的柄的上端处的突片，并且复合部件的至少一个帘布层表面图案接触并且基本上符合突片上的至少一个翼梁表面图案。 翼梁表面图案可以包括间隔开的翼梁表面突起，其间具有翼梁表面空间，并且翼梁表面突起从翼梁向外延伸并且布置在帘布层表面图案中的丝束之间。 拖车可以铺设在翼梁表面空间中。 翼梁表面图案可以包括连续的或分段间隔的翼梁表面突起和其间的翼梁表面空间，其间具有布置在翼梁表面空间中的帘布层表面图案中的丝束。 复合制品可以是包括复合翼型件的复合叶片或叶片。

    GAS TURBINE ENGINE WITH COMPOSITE AIRFOIL AND PREFORM CORE
    60.
    发明申请
    GAS TURBINE ENGINE WITH COMPOSITE AIRFOIL AND PREFORM CORE 有权

    公开(公告)号：US20250052162A1

    公开(公告)日：2025-02-13

    申请号：US18447525

    申请日：2023-08-10

    Applicant: GENERAL ELECTRIC COMPANY

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

    IPC: F01D5/28 ,  F02C3/04

    Abstract: A gas turbine engine includes a fan section, a compressor section, combustion section, and turbine section in serial flow arrangement, that defining an engine centerline extending between a forward direction and an aft direction. A composite component, such as an airfoil, extends between a root and a tip, defining a span-wise direction therebetween, and between a leading edge and a trailing edge, defining a chord-wise direction therebetween. The composite component includes a preform core including a first set of fibers as a first set of warp fibers and a first set of weft fibers.

Patent Agency Ranking