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    Apparatus for damping vibrations of the stator vanes of a gas turbine engine
    18.
    发明公开
    Apparatus for damping vibrations of the stator vanes of a gas turbine engine 审中-公开
    Vorrichtung zurDämpfungvon Vibrationen der Leitschaufel einer Gurburbine

    公开(公告)号：EP1586741A2

    公开(公告)日：2005-10-19

    申请号：EP05252332.1

    申请日：2005-04-14

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Cormier, Nathan Gerard ,  Rhoda, James Edwin ,  Manwaring, Steven Roy

    IPC: F01D9/04

    CPC classification number: F01D9/041 ,  F01D25/06 ,  F01D25/246 ,  F04D29/666 ,  F05D2240/129 ,  F05D2250/37 ,  F05D2260/961 ,  Y10T29/49323

    Abstract: A stator vane assembly (60) for a gas turbine engine includes a plurality of stator vane sectors (62), each of the plurality of stator vane sectors including an equal number of circumferentially-spaced stator vanes (34) oriented such that a first circumferential spacing (S 3 ) is defined between each pair of adjacent stator vanes within each sector. The plurality of stator vane sectors are coupled together such that a second circumferential spacing (S 4 ) is defined between each pair of adjacent stator vanes coupled to adjacent sectors. The second circumferential spacing is different from the first circumferential spacing.

    Abstract translation: 一种用于燃气涡轮发动机的定子叶片组件（60）包括多个定子叶片扇区（62），所述多个定子叶片扇区中的每一个包括相等数量的周向间隔开的定子叶片（34），所述定子叶片组件定向成使得第一圆周 在每个扇区内的每对相邻的定子叶片之间限定间隔（S 3）。 多个定子叶片扇区联接在一起，使得在耦合到相邻扇区的每对相邻的定子叶片之间限定第二周向间隔（S 4）。 第二周向间隔与第一周向间隔不同。

    Fan disk configuration
    19.
    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
    20.
    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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