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46 条记录 (耗时 0.015 秒)

    System for controlling thrust in steam turbine
    6.
    发明公开
    System for controlling thrust in steam turbine 有权
    系统zur Schubkontrolle在Dampfturbinen

    公开(公告)号：EP2426318A3

    公开(公告)日：2016-12-28

    申请号：EP11170837.6

    申请日：2011-06-21

    申请人： General Electric Company

    发明人： Zheng, Xiaoqing ,  Couture, Bernard Arthur, Jr. ,  Jones, Casey William ,  Roy, Binavak

    IPC分类号： F01D3/04 ,  F01D11/02 ,  F01D17/08 ,  F01D17/10 ,  F01D17/20 ,  F01D19/00 ,  F01D21/06 ,  F01D21/08 ,  F01D21/14

    CPC分类号： F01D11/025 ,  F01D3/04 ,  F01D17/08 ,  F01D17/10 ,  F01D17/20 ,  F01D19/00 ,  F01D21/06 ,  F01D21/08 ,  F01D21/14 ,  F05D2240/52

    摘要： A system controls net thrust of a steam turbine having a stepped rotating shaft. A first leak off line fluidly couples a first stage of a turbine section to a packing near a stepped portion on the rotating shaft. A second leak off line fluidly couples a second stage of the turbine section that has a pressure different from the first stage to a step area immediately adjacent to the stepped portion, and a connection line fluidly couples the first leak off line to the second leak off line. The lines include control valves such that a controller can actively control the net thrust by regulating thrust pressure on the stepped portion using steam from the first and second stages of the turbine section. The controller may also prevent damage to an active retractable seal using the control valves.

    摘要翻译： 系统控制具有阶梯式旋转轴的汽轮机的净推力。 第一泄漏线将涡轮机部分的第一级与旋转轴上的台阶部分附近的衬垫流体连接。 第二泄漏线将具有不同于第一级的压力的涡轮部分的第二级流体地联接到与阶梯部分紧邻的台阶区域，并且连接线将第一泄漏线与第二泄漏流体耦合 线。 这些管路​​包括控制阀，使得控制器可以通过使用来自涡轮部分的第一和第二级的蒸汽调节台阶部分上的推力来主动地控制净推力。 控制器还可以使用控制阀防止对活动的可缩回密封件的损坏。

    Apparatus for centering rotor assembly bearings
    8.
    发明公开
    Apparatus for centering rotor assembly bearings 审中-公开
    Vorrichtung zum Zentrieren einer Rotorlagerung

    公开(公告)号：EP1630357A2

    公开(公告)日：2006-03-01

    申请号：EP05255230.4

    申请日：2005-08-25

    申请人： GENERAL ELECTRIC COMPANY

    发明人： Allmon, Barry Lynn ,  Riffle, Richard Leon ,  Cabe, Jerry Lynn ,  Anstead, Duane Howard

    IPC分类号： F01D25/16 ,  F01D21/08

    CPC分类号： F01D25/164 ,  F05D2230/64 ,  F16C19/26 ,  F16C27/045 ,  F16C2360/23

    摘要： A bearing assembly for a gas turbine engine rotor (40) includes, an inner race (56), an outer race assembly (54), and a rolling element (52). The outer race assembly (54) includes a body, a plurality of first springs (104) attached to the body, and a plurality of second springs (106). Each first spring is radially aligned with a corresponding second spring forming a spring pair (120). The outer race assembly also includes a plurality of connecting members (108). Each connecting member extends between and connects a first end (112) of the first spring and a first end (122) of the second spring of said spring pair. The outer race assembly further includes a flange (126) with each second spring attached to the flange.

    摘要翻译： 用于燃气涡轮发动机转子（40）的轴承组件包括内圈（56），外座圈组件（54）和滚动元件（52）。 外圈组件（54）包括主体，附接到主体的多个第一弹簧（104）和多个第二弹簧（106）。 每个第一弹簧与形成弹簧对（120）的对应的第二弹簧径向对准。 外圈组件还包括多个连接构件（108）。 每个连接构件在第一弹簧的第一端（112）和所述弹簧对的第二弹簧的第一端（122）之间延伸并连接。 外圈组件还包括凸缘（126），每个第二弹簧连接到凸缘。

    SEAL ASSEMBLY FOR A GAS TURBINE ENGINE
    10.
    发明公开
    SEAL ASSEMBLY FOR A GAS TURBINE ENGINE 审中-公开

    公开(公告)号：EP3828391A3

    公开(公告)日：2021-09-29

    申请号：EP20208790.4

    申请日：2020-11-20

    申请人： Raytheon Technologies Corporation

    发明人： LUTJEN, Paul M. ,  THILL, Carson A. Roy

    IPC分类号： F01D11/00 ,  F01D21/08 ,  F01D25/24 ,  F01D11/12

    摘要： An assembly (60) for a gas turbine engine (20) comprising a component (66) that has a first interface portion (74), and a support (68) that has a mounting portion (76) and a second interface portion (78), the mounting portion (76) attachable to an engine static structure (36), a first retention feature (80) that releasably secures the first interface portion (74) to the support (68) in a first installed position of the gas turbine engine component (66), and a second retention feature (82) dimensioned to secure the first interface portion (74) to the second interface portion (78) in a second installed position of the gas turbine engine component (66). The first installed position differs from the second installed position, and one of first and second retention features is dimensioned to carry the gas turbine engine component (66) in response to release of another one of the first and second retention features.