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74 条记录 (耗时 0.019 秒)

    Combustor liner helical cooling apparatus
    2.
    发明授权
    Combustor liner helical cooling apparatus 有权
    燃烧室衬里螺旋冷却装置

    公开(公告)号：EP2375156B1

    公开(公告)日：2017-12-27

    申请号：EP11161628.0

    申请日：2011-04-08

    申请人： General Electric Company

    发明人： McMahan, Kevin Weston ,  Chila, Ronald James

    IPC分类号： F23M5/08 ,  F23R3/00

    CPC分类号： F23M5/085 ,  F23R3/002 ,  F23R2900/03043 ,  F23R2900/03045

    摘要： A combustor liner (34) is provided. The combustor liner (34) may include an upstream portion (51) and a downstream end portion (52). The upstream portion (51) may have a radius (R1) and a length (L1) along a generally longitudinal axis (58). The downstream end portion (52) may have a radius (R2) and a length (L2) along the generally longitudinal axis (58). The downstream end portion (52) may define a plurality of channels (56). Each of the plurality of channels (56) may extend helically through the length (98) of the downstream end portion (52). Each of the plurality of channels (56) may be configured to flow an air flow (84) therethrough, cooling the downstream end portion (52).

    Turbine system comprising a transition duct
    4.
    发明公开
    Turbine system comprising a transition duct 审中-公开
    Turbinensystem mit einemÜbergangskanal

    公开(公告)号：EP2578808A2

    公开(公告)日：2013-04-10

    申请号：EP12186896.2

    申请日：2012-10-01

    申请人： General Electric Company

    发明人： McMahan, Kevin Weston ,  Dillard, Daniel Jackson

    IPC分类号： F01D9/02

    CPC分类号： F01D9/023 ,  F01D5/186 ,  F01D5/187 ,  F05D2300/6033

    摘要： A turbine system is disclosed. The turbine system (10) includes a transition duct (50) having an inlet (52), an outlet (54), and a passage (56) extending between the inlet (52) and the outlet (54) and defining a longitudinal axis (90), a radial axis (94), and a tangential axis (92). The outlet (54) of the transition duct (50) is offset from the inlet (52) along the longitudinal axis (90) and the tangential axis (92). The turbine system further includes a turbine section (16) connected to the transition duct (50). The turbine section includes a plurality of shroud blocks at least partially defining a hot gas path, a plurality of buckets at least partially disposed in the hot gas path, and a plurality of nozzles at least partially disposed in the hot gas path. At least one of a shroud block, a bucket, or a nozzle includes means for withstanding high temperatures.

    摘要翻译： 公开了一种涡轮机系统。 涡轮系统（10）包括具有入口（52），出口（54）和在入口（52）和出口（54）之间延伸的通道（56））的过渡管道（50），并且限定纵向轴线 （90），径向轴线（94）和切线轴线（92）。 过渡管道（50）的出口（54）沿着纵向轴线（90）和切线轴线（92）偏离入口（52）。 涡轮机系统还包括连接到过渡管道（50）的涡轮机部分（16）。 涡轮部分包括至少部分地限定热气体路径的多个护罩块，至少部分地设置在热气体路径中的多个桶，以及至少部分地设置在热气体路径中的多个喷嘴。 护罩块，铲斗或喷嘴中的至少一个包括耐高温的装置。

    Systems and methods for reintroducing gas turbine combustion bypass flow
    5.
    发明公开
    Systems and methods for reintroducing gas turbine combustion bypass flow 审中-公开
    系统与Verfahren zur Wiedereinleitung des Bypass-Stroms einer Gasturbinenverbrennung

    公开(公告)号：EP2230457A2

    公开(公告)日：2010-09-22

    申请号：EP10156373.2

    申请日：2010-03-12

    申请人： General Electric Company

    发明人： McMahan, Kevin Weston ,  Johnson, Thomas Edward ,  Widener, Stanley Kevin

    IPC分类号： F23R3/26 ,  F23R3/04

    CPC分类号： F23R3/26 ,  F23R3/04

    摘要： A system and method for reintroducing gas turbine combustion bypass flow. The system may include a combustor body (11), wherein the combustor body (11) includes a reaction zone (15) for primary combustion of fuel and air, and a casing (12) enclosing the combustor body (11) and defining an annular passageway (13) for carrying compressor discharge air into the combustor body (11) at one end (14). The system further may include a reintroduction manifold (19) for receiving combustor bypass air extracted from the compressor discharge air in the annular passageway (13), and one or more reintroduction slots in communication with the reintroduction manifold (19) for injecting the combustor bypass air into the combustor body (11) downstream of the reaction zone (15). The method may include extracting combustor bypass air from the annular passageway (13), transporting the combustor bypass air to a reintroduction manifold (19), and reintroducing the combustor bypass air into the combustor body (11) through one or more reintroduction slots in communication with the reintroduction manifold (19).

    摘要翻译： 一种用于重新引入燃气轮机燃烧旁路流的系统和方法。 该系统可以包括燃烧器主体（11），其中燃烧器主体（11）包括用于燃料和空气的初级燃烧的反应区（15）和封闭燃烧器主体（11）并限定环形 用于在一端（14）处将压缩机排放到燃烧器主体（11）中的通道（13）。 该系统还可以包括用于接收从环形通道（13）中的压缩机排放空气抽出的燃烧器旁路空气的再引入歧管（19），以及与再引入歧管（19）连通的一个或多个再引入槽，用于喷射燃烧器旁路 空气进入反应区（15）下游的燃烧器体（11）。 该方法可以包括从环形通道（13）提取燃烧器旁路空气，将燃烧器旁路空气输送到重新引入歧管（19），并且通过一个或多个通信中的再引入槽将燃烧器旁路空气重新引入燃烧器主体（11） 与重新引入歧管（19）。

    Seal retainer assembly
    8.
    发明公开
    Seal retainer assembly 有权
    密封夹具

    公开(公告)号：EP1108901A3

    公开(公告)日：2002-07-17

    申请号：EP00311266.1

    申请日：2000-12-15

    申请人： GENERAL ELECTRIC COMPANY

    发明人： Rainous, Edward Atwood ,  Barber, Daniel John ,  Vickers, Edward Charles ,  Maue, Gregory Paul ,  Cody, William Edward ,  Yee, Sharon Lisa ,  McMahan, Kevin Weston

    IPC分类号： F16B37/08 ,  F16B5/02

    CPC分类号： F01D25/246 ,  F01D11/001 ,  F04D29/164 ,  F16B5/0241

    摘要： A retainer (82), in an exemplary embodiment of the invention, is used in a gas turbine engine inter-stage seal assembly to retain an annular seal ring flange (50) of a seal ring (48) against an annular platform flange (60) extending radially inwardly from an inner platform (30) of an annular nozzle stage having nozzle vanes (26). The retainer includes a body having a central portion (92) through which a bore (88) is formed around a bore axis (89) and a central tab (94) extends radially outwardly from the central portion (92) with respect to the bore axis (89). First and second arms (97 and 98), respectively, extend in opposite respective first and second tangential directions, with respect to the bore axis (89), away from the central portion (92) and each other. Axial spacers (104) extend aftwardly from first and second free ends (106 and 108) of the first and second arms (97 and 98), respectively and anti-rotation feet with rounded ends depend from the first and second free ends (106 and 108) in an opposite direction from which the central tab (94) extends. A pedestal assembly (110) extends aft from the central portion (92) and is located aft of the central tab. The retainer (82) is an integrally cast unit.