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    Snap-on turbineblade shim
    2.
    发明公开
    Snap-on turbineblade shim 有权
    Zwischenstückmit Schnappverbindungfüreine Turbinenschaufel

    公开(公告)号：EP1443180A2

    公开(公告)日：2004-08-04

    申请号：EP04250460.5

    申请日：2004-01-28

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Forrester, James Michael ,  Grant, Robert Russell ,  Higgins, Craig William ,  Clausing, Emily Anne ,  Cargill, John Gregory

    IPC: F01D5/30

    CPC classification number: F01D5/3092 ,  F05D2250/00

    Abstract: A gas turbine engine blade root shim includes a dovetail shim portion with a dovetail shape and a longitudinally extending substantially flat base (52) and distal first and second longitudinally spaced apart forward and aft ends (72 and 76). Transversely spaced apart first and second walls (54 and 64) extend upwardly from the base (52) which includes at least two longitudinally extending elongated base apertures (90). Each of the base apertures (90) includes a main region (92) and longitudinally spaced apart rounded end regions (94). Dog-bone-shaped base apertures or rounded end base apertures having semi-circular rounded end regions may be used. The shim is designed for a blade dovetail root with a root slot formed in a bottom of the dovetail root. The dovetail shim portion with the dovetail shape substantially conforms to at least a portion of a cross-sectional dovetail shape of the dovetail root through the root slot. The base (52) is disposed within the root slot.

    Abstract translation: 燃气涡轮发动机叶片根垫片包括燕尾形垫片部分，其具有燕尾形状和纵向延伸的基本上平坦的基部（52）和远侧的第一和第二纵向间隔开的前后端部（72和76）。 横向间隔开的第一和第二壁（54和64）从基部（52）向上延伸，其包括至少两个纵向延伸的细长基部孔（90）。 每个基座孔（90）包括主区域（92）和纵向间隔开的圆形端部区域（94）。 可以使用具有半圆形圆形端部区域的狗骨形基部孔或圆形端部基部孔。 垫片设计用于具有形成在燕尾根底部的根槽的叶片燕尾根。 具有燕尾形状的燕尾形垫片部分基本上符合燕尾根的横截面燕尾形状的至少一部分，通过根槽。 基部（52）设置在根槽内。

    Snap-on turbineblade shim
    3.
    发明公开
    Snap-on turbineblade shim 有权
    适配器具有用于涡轮机叶片卡扣连接

    公开(公告)号：EP1443180A3

    公开(公告)日：2006-06-28

    申请号：EP04250460.5

    申请日：2004-01-28

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Forrester, James Michael ,  Grant, Robert Russell ,  Higgins, Craig William ,  Clausing, Emily Anne ,  Cargill, John Gregory

    IPC: F01D5/30

    CPC classification number: F01D5/3092 ,  F05D2250/00

    Abstract: A gas turbine engine blade root shim includes a dovetail shim portion with a dovetail shape and a longitudinally extending substantially flat base (52) and distal first and second longitudinally spaced apart forward and aft ends (72 and 76). Transversely spaced apart first and second walls (54 and 64) extend upwardly from the base (52) which includes at least two longitudinally extending elongated base apertures (90). Each of the base apertures (90) includes a main region (92) and longitudinally spaced apart rounded end regions (94). Dog-bone-shaped base apertures or rounded end base apertures having semi-circular rounded end regions may be used. The shim is designed for a blade dovetail root with a root slot formed in a bottom of the dovetail root. The dovetail shim portion with the dovetail shape substantially conforms to at least a portion of a cross-sectional dovetail shape of the dovetail root through the root slot. The base (52) is disposed within the root slot.

    Blade insert
    5.
    发明公开
    Blade insert 有权
    Einsatzstück

    公开(公告)号：EP1209322A2

    公开(公告)日：2002-05-29

    申请号：EP01309913.0

    申请日：2001-11-26

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Forrester, James Michael

    IPC: F01D5/30

    CPC classification number: F01D5/323 ,  F05D2250/71 ,  F05D2300/431 ,  Y02T50/671 ,  Y02T50/673 ,  Y10S416/50

    Abstract: An exemplary embodiment of the invention is a gas turbine engine blade spacer has an axially extending backbone (300), spaced apart forward, mid and aft dovetail lands (302, 304 and 308), respectively, disposed along the backbone, the backbone (300) and the forward, mid, and aft dovetail lands (302, 304 and 308) having bottom curved backbone surfaces (310). Each of the forward, mid and aft dovetail lands has a riser (312) that extends above the backbone (300) and has a riser flat top (314). In the exemplary embodiment disclosed herein, a spacer tab (320) extends generally axially forward of the forward land (302) and includes intersecting axially and radially extending tab apertures (316 and 318). A void (330) extends around the backbone (300) and between the forward and aft dovetail lands (302 and 308) and the void filled with an elastomeric material (332). The spacer has a constant shape and size cross-section between the forward and aft dovetail lands. The invention has a particular use with circular arc dovetail slots and roots for which the spacer is a circular arc shaped spacer and the backbone (300), and the forward, mid and aft dovetail lands (302, 304 and 308) are curved along a circular arc normal to and about a radial axis (RA). The spacer tab (320) has a rectangular cross-section (321), extends axially out of a forward face (322) of the forward land (302), and has a tab flat top (324) that is co-planar with the riser flat tops (314) of the risers (312).

    Abstract translation: 本发明的一个示例性实施例是燃气涡轮发动机叶片间隔件具有轴向延伸的主干（300），分别沿着骨架设置的间隔开的前，中，后燕尾平台（302,304和308），骨架（300） ）和具有底部弯曲主干表面（310）的前，中，后燕尾地（302,304和308）。 每个前，后，后燕尾地具有在主干（300）上方延伸并具有立管平顶（314）的提升管（312）。 在本文公开的示例性实施例中，间隔片突出部（320）大致轴向地延伸到前部平台（302）的前方并且包括相交的轴向和径向延伸的突片孔（316和318）。 空隙（330）围绕主干（300）延伸并且在前后燕尾槽脊（302和308）之间以及填充有弹性材料（332）的空隙之间延伸。 间隔物在前燕尾燕尾缘之间具有恒定的形状和尺寸的横截面。 本发明具有圆弧燕尾槽和根的特殊用途，其中间隔件是圆弧形间隔件和主体（300），并且前，中，后燕尾榫（302,304和308）沿着 垂直于径向轴线（RA）的圆弧。 间隔片（320）具有矩形横截面（321），其从正向平台（302）的前表面（322）轴向延伸，并且具有与该平坦顶部（324）共面 立管（312）的立管平顶（314）。

    Fan disk configuration
    6.
    发明公开
    Fan disk configuration 有权
    疤痕磁盘配置用于风扇转子

    公开(公告)号：EP1209320A3

    公开(公告)日：2003-10-15

    申请号：EP01309912.2

    申请日：2001-11-26

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Forrester, James Michael ,  Bolt, Janine Elizabeth ,  Rhoda, James Edwin ,  Stevenson, Joseph Timothy

    IPC: F01D5/02 ,  F01D21/04 ,  F01D5/30

    CPC classification number: F01D5/326 ,  F01D5/06 ,  F01D11/008 ,  F01D21/045 ,  F05D2250/141 ,  Y02T50/671 ,  Y02T50/673

    Abstract: A gas turbine engine rotor disk (16) has a number of annular hubs (64) circumscribed about a centerline and each of the hubs is connected to a disk rim by a web (68). A plurality of circumferentially spaced apart dovetail slots are disposed through the rim (62), extending circumferentially between disk posts (50), extending axially from a forward end (65) to an aft end (67) of the rim, and extending radially inwardly from a disk outer surface (63) of the rim. Circumferentially extending annular burst slots (70) extend radially through the rim (62) into the dovetail slots between each adjacent pair (72) of the webs (68). In the exemplary embodiment of the invention illustrated herein, the dovetail slots are circular arc dovetail slots. An axially forwardly extending overhang (69) is located radially outwardly on each of the disk posts (50) and a chamfer (39) is on a radially outer corner (45) of the each of the disk posts (50) on a portion of the overhangs (69). A plurality of post holes extending axially aftwardly into the rim (62) wherein each of the post hole extends axially aftwardly into a corresponding one of the disk posts (50).

    Fan disk configuration
    7.
    发明公开
    Fan disk configuration 有权
    NarbenscheibenkonfigurationfüreinenBläserrotor

    公开(公告)号：EP1209320A2

    公开(公告)日：2002-05-29

    申请号：EP01309912.2

    申请日：2001-11-26

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Forrester, James Michael ,  Bolt, Janine Elizabeth ,  Rhoda, James Edwin ,  Stevenson, Joseph Timothy

    IPC: F01D5/02 ,  F01D21/04

    CPC classification number: F01D5/326 ,  F01D5/06 ,  F01D11/008 ,  F01D21/045 ,  F05D2250/141 ,  Y02T50/671 ,  Y02T50/673

    Abstract: A gas turbine engine rotor disk (16) has a number of annular hubs (64) circumscribed about a centerline and each of the hubs is connected to a disk rim by a web (68). A plurality of circumferentially spaced apart dovetail slots are disposed through the rim (62), extending circumferentially between disk posts (50), extending axially from a forward end (65) to an aft end (67) of the rim, and extending radially inwardly from a disk outer surface (63) of the rim. Circumferentially extending annular burst slots (70) extend radially through the rim (62) into the dovetail slots between each adjacent pair (72) of the webs (68). In the exemplary embodiment of the invention illustrated herein, the dovetail slots are circular arc dovetail slots. An axially forwardly extending overhang (69) is located radially outwardly on each of the disk posts (50) and a chamfer (39) is on a radially outer corner (45) of the each of the disk posts (50) on a portion of the overhangs (69). A plurality of post holes extending axially aftwardly into the rim (62) wherein each of the post hole extends axially aftwardly into a corresponding one of the disk posts (50).

    Abstract translation: 燃气涡轮发动机转子盘（16）具有围绕中心线限定的多个环形轮毂（64），并且每个轮毂通过腹板（68）连接到盘形边缘。 多个沿周向间隔开的燕尾槽设置成穿过边缘（62），沿圆周方向延伸，在圆柱（50）之间沿轴向从边缘的前端（65）延伸到后端（67），并且径向向内延伸 从轮辋的盘外表面（63）。 圆周延伸的环形突出槽（70）径向延伸穿过边缘（62）进入腹板（68）的每个相邻对（72）之间的燕尾槽。 在本文所示的本发明的示例性实施例中，燕尾槽是圆弧燕尾槽。 轴向向前延伸的突出部分（69）位于每个盘柱（50）的径向外侧，倒角（39）位于每个盘柱（50）的径向外角（45）上， 悬垂（69）。 多个沿轴向向后延伸到边缘（62）中的柱孔，其中每个柱孔轴向向后延伸到相应的一个盘柱（50）中。

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