利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

359 条记录 (耗时 0.02 秒)

    Discrete load fin for individual stator vane
    51.
    发明专利
    Discrete load fin for individual stator vane 有权
    独立定位器的离散负载

    公开(公告)号：JP2010169088A

    公开(公告)日：2010-08-05

    申请号：JP2010007656

    申请日：2010-01-18

    申请人： General Electric Co ,  ゼネラル・エレクトリック・カンパニイGeneral Electric Company

    发明人： KASPERSKI DONALD JOSEPH

    IPC分类号： F04D29/54 ,  F01D9/02 ,  F01D9/04 ,  F04D19/02

    CPC分类号： F01D9/042 ,  F01D9/04 ,  F01D9/041 ,  F01D25/24 ,  F01D25/246 ,  F01D25/26 ,  F04D29/542 ,  Y02T50/673

    摘要： PROBLEM TO BE SOLVED: To provide a turbine engine in which a force load of stator blades is consistent.
    SOLUTION: The turbine engine (10) has a circumferential casing (22) with a circumferentially extending slot (28) formed in an inner wall (30). A radially inwardly facing fin-ring (33) is disposed in the slot (28) and has a radially inwardly projecting fin (44) extending axially there across. A radially inwardly extending stator blade (34) has a base (36) and an airfoil (38). The base (36) is disposed in the casing slot (28), radially inwardly of the fin-ring (33). A complementary base slot (46) is disposed on the stator blade base (36) and is configured to receive the fin (44) therein for transferring a circumferential force, applied to the stator blade (34), to the fin-ring (33).
    COPYRIGHT: (C)2010,JPO&INPIT

    摘要翻译： 要解决的问题：提供一种其中定子叶片的力载荷一致的涡轮发动机。 解决方案：涡轮发动机（10）具有周向壳体（22），其周向延伸的槽（28）形成在内壁（30）中。 径向向内的翅片环（33）设置在槽（28）中并且具有沿轴向延伸的径向向内突出的翅片（44）。 径向向内延伸的定子叶片（34）具有基座（36）和翼型件（38）。 基部（36）在翅片环（33）的径向内侧设置在壳体狭槽（28）中。 互补的基座槽（46）设置在定子叶片基座（36）上并且构造成在其中容纳翅片（44），以将施加到定子叶片（34）的周向力传递到翅片环（33） ）。 版权所有（C）2010，JPO＆INPIT

    Shroud for turbo machine
    53.
    发明专利
    Shroud for turbo machine 有权
    涡轮机SHROUD

    公开(公告)号：JP2010065698A

    公开(公告)日：2010-03-25

    申请号：JP2009207666

    申请日：2009-09-09

    申请人： General Electric Co ,  ゼネラル・エレクトリック・カンパニイGeneral Electric Company

    发明人： TAGIR ROBERT NIGMATULIN ,  BULGRIN CHARLES A ,  KELLOCK IAIN ROBERTSON ,  BRUNER RALPH CHRIS

    IPC分类号： F01D25/24 ,  F01D11/02 ,  F02C7/28 ,  F16J15/447

    CPC分类号： F01D9/04 ,  F01D11/02 ,  F01D25/246

    摘要： PROBLEM TO BE SOLVED: To provide a shroud for a turbo machine reducing air leak into a high temperature gas passage through a gap.
    SOLUTION: The turbo machine (2) includes a casing (4) defining the hot gas path (12), and a shroud member (48) attached to the casing (4). The shroud member (48) separates from the casing (4) and defines the gap. The shroud member includes a first end part (76) including a first hook member (90) provided with a first seal surface, and a second end part (77) including a second hook member (95) provided with a second seal surface (97). At least one of a first and a second seal surface (92, 97) includes a plurality of labyrinth seal element (110-116) reducing air leak into the hot gas path (12) through the gap.
    COPYRIGHT: (C)2010,JPO&INPIT

    摘要翻译： 要解决的问题：提供一种用于涡轮机的护罩，其将空气泄漏减少到通过间隙的高温气体通道中。 解决方案：涡轮机（2）包括限定热气路径（12）的壳体（4）和附接到壳体（4）的护罩构件（48）。 护罩构件（48）与壳体（4）分离并限定间隙。 护罩构件包括第一端部（76），第一端部（76）包括设置有第一密封表面的第一钩构件（90）和包括第二钩构件（95）的第二端部（77），第二钩构件设置有第二密封表面 ）。 第一和第二密封表面（92,97）中的至少一个包括多个迷宫式密封元件（110-116），其通过间隙减少进入热气体通道（12）的空气泄漏。 版权所有（C）2010，JPO＆INPIT

    Divergent turbine nozzle
    55.
    发明专利
    Divergent turbine nozzle 有权
    DIVERGENT涡轮喷嘴

    公开(公告)号：JP2009144724A

    公开(公告)日：2009-07-02

    申请号：JP2008317782

    申请日：2008-12-15

    申请人： General Electric Co ,  ゼネラル・エレクトリック・カンパニイGeneral Electric Company

    发明人： BROOMER MARK ,  CORREIA VICTOR HUGO SILVA ,  MANNING ROBERT FRANCIS ,  TUNG STEPHEN KIN-KEUNG ,  REDDY BHANU MAHASAMUDRAM

    IPC分类号： F01D9/02 ,  F02C7/18

    CPC分类号： F01D9/04 ,  F01D25/12 ,  F05D2250/324 ,  F05D2260/202 ,  Y02T50/676

    摘要： PROBLEM TO BE SOLVED: To provide a divergent turbine nozzle, in a turbine nozzle in a gas turbine engine.
    SOLUTION: The turbine nozzle 22 includes a row of vanes 32 extending radially over a span between inner and outer bands 34, 36. The vanes 32 include opposite pressure and suction sidewalls 38, 40 and opposite leading and trailing edges 42, 44. Each vane 32 includes an inner pattern of inner cooling holes 52 and an outer pattern of outer cooling holes 54 distributed along the leading edge 42. The inner and outer holes 52, 54 selectively diverge and discharge cooling air toward the corresponding inner and outer bands 34, 36.
    COPYRIGHT: (C)2009,JPO&INPIT

    摘要翻译： 要解决的问题：在燃气涡轮发动机的涡轮喷嘴中提供发散的涡轮喷嘴。 解决方案：涡轮喷嘴22包括一排叶片32，其沿径向延伸在内带34和外带36之间的跨度上。叶片32包括相对的压力和吸力侧壁38,40以及相对的前缘和后缘42,44 每个叶片32包括内部冷却孔52的内部图案和沿着前缘42分布的外部冷却孔54的外部图案。内部和外部孔52,54选择性地将冷却空气朝向相应的内部和外部带 34，36.版权所有（C）2009，JPO＆INPIT

    Thermally compliant clip
    60.
    发明专利
    Thermally compliant clip 有权
    热合并夹

    公开(公告)号：JP2007046603A

    公开(公告)日：2007-02-22

    申请号：JP2006213030

    申请日：2006-08-04

    申请人： General Electric Co ,  ゼネラル・エレクトリック・カンパニイGeneral Electric Company

    发明人： RUTHEMEYER MICHAEL A ,  NICHOLS GLENN HERBERT ,  LEE CHING-PANG

    IPC分类号： F02C7/28 ,  F01D11/08

    CPC分类号： F01D9/04 ,  F05D2230/60 ,  F05D2240/11 ,  F05D2260/30 ,  F05D2260/941

    摘要： PROBLEM TO BE SOLVED: To provide a C-clip for a gas turbine engine.
    SOLUTION: The C-clip 56 includes an outer arcuate arm 60 having a first radius of curvature; an inner arcuate arm 58 having a second radius of curvature which is substantially greater than the first radius of curvature; and an arcuate flange 57 connecting the outer arcuate arm 60 and the inner arcuate arm 58. The flange 57, the outer arcuate arm 60, and the inner arcuate arm 58 collectively define a substantially C-shaped cross section. A shroud assembly 33 includes a shroud segment 32 with a mounting flange 54, and a shroud hanger with an arcuate hook 44 disposed in mating relationship to the mounting flange 54. The arcuate C-clip 56 having the inner and outer arcuate arms 56, 60, overlaps the hook 44 and the mounting flange 54. The shroud segment 32 and the C-clip 56 are subject to thermal expansion at a hot operating condition. One of the dimensions of the shroud segment 32 and the C-clip 58 is selected to produce a preselected dimensional relationship between them at the hot operating condition.
    COPYRIGHT: (C)2007,JPO&INPIT

    摘要翻译： 要解决的问题：提供一种用于燃气涡轮发动机的C形夹。 解决方案：C形夹56包括具有第一曲率半径的外弧形臂60; 具有基本上大于第一曲率半径的第二曲率半径的内弓形臂58; 以及连接外弓形臂60和内弓形臂58的弓形凸缘57.凸缘57，外弓形臂60和内弓形臂58共同限定大致C形横截面。 护罩组件33包括具有安装凸缘54的护罩段32和具有与安装凸缘54成配合关系设置的弓形钩44的护罩悬挂件。具有内和外弓形臂56,60的弓形C形夹56 与钩44和安装凸缘54重叠。护罩段32和C形夹56在热操作状态下经受热膨胀。 选择护罩段32和C形夹58的尺寸之一以在热操作状态下在它们之间产生预选的尺寸关系。 版权所有（C）2007，JPO＆INPIT