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    RING SEGMENT WITH SERPENTINE COOLING PASSAGES
    31.
    发明申请
    RING SEGMENT WITH SERPENTINE COOLING PASSAGES 审中-公开
    带有SERPENTINE冷却通道的环形分段

    公开(公告)号：WO2012033643A1

    公开(公告)日：2012-03-15

    申请号：PCT/US2011/049100

    申请日：2011-08-25

    Applicant: SIEMENS ENERGY, INC. ,  LEE, Ching-Pang ,  BERRONG, Eric C.

    Inventor： LEE, Ching-Pang ,  BERRONG, Eric C.

    IPC: F01D11/08

    CPC classification number: F01D11/08 ,  F05D2250/70 ,  F05D2260/20

    Abstract: A ring segment for a gas turbine engine includes a panel and a cooling system. The cooling system receives cooling fluid from an outer side of the panel for cooling the panel and includes at least one cooling fluid supply passage, at least one serpentine cooling passage, and at least one cooling fluid discharge passage. The cooling fluid supply passage(s) receive the cooling fluid from the outer side of the panel and deliver the cooling fluid to a first cooling fluid chamber within the panel. The serpentine cooling passage(s) receive the cooling fluid from the first cooling fluid chamber, wherein the cooling fluid provides convective cooling to the panel as it passes through the serpentine cooling passage(s). The cooling fluid discharge passage(s) discharge the cooling fluid from the cooling system.

    Abstract translation: 用于燃气涡轮发动机的环段包括面板和冷却系统。 冷却系统从面板的外侧接收冷却流体，用于冷却面板，并且包括至少一个冷却流体供应通道，至少一个蛇形冷却通道和至少一个冷却流体排出通道。 冷却流体供应通道从面板的外侧接收冷却流体，并将冷却流体输送到面板内的第一冷却流体室。 蛇形冷却通道从第一冷却流体室接收冷却流体，其中冷却流体在通过蛇形冷却通道时向面板提供对流冷却。 冷却流体排出通道从冷却系统排出冷却流体。

    FILM COOLED COMPONENT WALL IN A TURBINE ENGINE
    32.
    发明申请
    FILM COOLED COMPONENT WALL IN A TURBINE ENGINE 审中-公开
    涡轮发动机中的薄膜冷却组件墙

    公开(公告)号：WO2011156805A1

    公开(公告)日：2011-12-15

    申请号：PCT/US2011/040162

    申请日：2011-06-13

    Applicant: SIEMENS ENERGY, INC. ,  LEE, Ching-Pang ,  UM, Jae Y. ,  MUNSHI, Mrinal ,  ZUNIGA, Humberto A.

    Inventor： LEE, Ching-Pang ,  UM, Jae Y. ,  MUNSHI, Mrinal ,  ZUNIGA, Humberto A.

    IPC: F01D5/18 ,  F01D25/12 ,  F01D5/28 ,  F01D5/20

    CPC classification number: F01D5/186 ,  F01D5/288 ,  F01D25/12 ,  F05D2230/10 ,  F05D2230/30 ,  F05D2230/90 ,  F05D2250/183 ,  F05D2250/185 ,  F05D2260/202 ,  F05D2260/221 ,  F05D2300/502 ,  F23R2900/03042 ,  Y10T29/49236

    Abstract: A component wall in a turbine engine. The component wall includes a substrate, a trench, and a plurality of cooling passages. The substrate has a first surface and a second surface opposed from the first surface. The trench is located in the second surface and is defined by a bottom surface between the first and second surfaces, a first sidewall, and a second sidewall spaced from the first sidewall. The first sidewall extends radially outwardly continuously from the bottom surface of the trench to the second surface. The first sidewall includes a plurality of first protuberances extending toward the second sidewall. The cooling passages extend through the substrate from the first surface to the bottom surface of the trench. Outlets of the cooling passages are arranged within the trench such that cooling air exiting the cooling passages is directed toward respective ones of the first protuberances

    Abstract translation: 涡轮发动机中的部件壁。 部件壁包括基板，沟槽和多个冷却通道。 基板具有与第一表面相对的第一表面和第二表面。 沟槽位于第二表面中，并且由第一和第二表面之间的底表面，第一侧壁和与第一侧壁间隔开的第二侧壁限定。 第一侧壁从沟槽的底表面连续径向向外延伸到第二表面。 第一侧壁包括朝向第二侧壁延伸的多个第一突起。 冷却通道从沟槽的第一表面延伸到底表面。 冷却通道的出口布置在沟槽内，使得离开冷却通道的冷却空气被引向第一突起

    TURBINE BLADE WITH INTEGRATED SERPENTINE AND AXIAL TIP COOLING CIRCUITS
    38.
    发明申请
    TURBINE BLADE WITH INTEGRATED SERPENTINE AND AXIAL TIP COOLING CIRCUITS 审中-公开
    具有集成SERPENTINE和轴向冷却电路的涡轮叶片

    公开(公告)号：WO2014113162A3

    公开(公告)日：2014-12-11

    申请号：PCT/US2013075034

    申请日：2013-12-13

    Applicant: SIEMENS AG ,  LEE CHING-PANG

    Inventor： LEE CHING-PANG

    IPC: F01D5/18 ,  F01D5/20

    CPC classification number: F01D5/187 ,  F01D5/186 ,  F01D5/20 ,  F05D2240/307 ,  F05D2250/185 ,  F05D2250/75 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/2212 ,  F05D2260/2214

    Abstract: An air cooled turbine blade (10) including leading and trailing edges (22, 24), and pressure and suction side walls (18, 20) extending between the leading and trailing edges. Leading and trailing edge cooling circuits (34, 36) extend spanwise adjacent to the leading and trailing edges, respectively. A forward flow mid-section serpentine cooling circuit (38) extends spanwise and is located between the leading and trailing edge cooling circuits. An axial tip cooling circuit (40) extends in the chordal direction and is located between a tip cap of the blade and the serpentine cooling circuit at an outer end of the serpentine cooling circuit. The axial tip cooling circuit has a forward end (41) receiving cooling air from a final channel (62) of the serpentine cooling circuit and discharges the cooling air adjacent to the trailing edge. A method for cooling a corresponding turbine blade (10).

    Abstract translation: 包括前缘和后缘（22,24）的空气冷却涡轮机叶片（10）以及在前缘和后缘之间延伸的压力和吸力侧壁（18,20）。 前缘和后缘冷却回路（34,36）分别沿着前缘和后缘分别延伸。 向前流动的中段蛇形冷却回路（38）沿翼展方向延伸并且位于前缘和后缘冷却回路之间。 轴向末端冷却回路（40）在弦线方向上延伸，位于蛇形冷却回路的外端处，位于叶片的顶盖和蛇形冷却回路之间。 轴向末端冷却回路具有从蛇形冷却回路的最终通道（62）接收冷却空气的前端（41）并排出与后缘相邻的冷却空气。 一种用于冷却相应的涡轮叶片（10）的方法。

    SEAL ASSEMBLY INCLUDING GROOVES IN A RADIALLY OUTWARDLY FACING SIDE OF A PLATFORM IN A GAS TURBINE ENGINE
    39.
    发明申请
    SEAL ASSEMBLY INCLUDING GROOVES IN A RADIALLY OUTWARDLY FACING SIDE OF A PLATFORM IN A GAS TURBINE ENGINE 审中-公开
    密封组件包括在气体涡轮发动机中的平台的径向外侧面上的格栅

    公开(公告)号：WO2014143413A2

    公开(公告)日：2014-09-18

    申请号：PCT/US2014/012525

    申请日：2014-01-22

    Applicant: SIEMENS AKTIENGESELLSCHAFT ,  LEE, Ching-Pang

    Inventor： LEE, Ching-Pang

    CPC classification number: F01D11/001 ,  F01D11/02 ,  F05D2240/80 ,  F05D2250/37 ,  F05D2250/38 ,  F05D2250/71 ,  F05D2260/14

    Abstract: A seal assembly between a disc cavity and a turbine section hot gas path includes a stationary vane assembly and a rotating blade assembly downstream from the vane assembly and including a plurality of blades that are supported on a platform and rotate with a turbine rotor and the platform during operation of the engine. The platform includes a radially outwardly facing first surface, a radially inwardly facing second surface, a third surface, and a plurality of grooves extending into the third surface. The grooves are arranged such that a space is defined between adjacent grooves. During operation of the engine, the grooves guide purge air out of the disc cavity toward the hot gas path such that the purge air flows in a desired direction with reference to a direction of hot gas flow through the hot gas path.

    Abstract translation: 在盘腔和涡轮部分热气路径之间的密封组件包括固定叶片组件和在叶片组件下游的旋转叶片组件，并且包括支撑在平台上并与涡轮机转子和平台一起旋转的多个叶片 在发动机运行期间。 平台包括径向向外的第一表面，径向向内的第二表面，第三表面和延伸到第三表面中的多个凹槽。 凹槽被布置成使得在相邻凹槽之间限定空间。 在发动机操作期间，凹槽将吹扫空气从盘腔朝向热气路径引导，使得净化空气相对于热气流通过热气路径的方向在所需方向上流动。

    METHOD FOR OPERATING A GAS TURBINE ENGINE INCLUDING A COMBUSTOR SHELL AIR RECIRCULATION SYSTEM
    40.
    发明申请
    METHOD FOR OPERATING A GAS TURBINE ENGINE INCLUDING A COMBUSTOR SHELL AIR RECIRCULATION SYSTEM 审中-公开
    用于操作气体涡轮发动机的方法，包括燃气轮机空气再循环系统

    公开(公告)号：WO2014039315A1

    公开(公告)日：2014-03-13

    申请号：PCT/US2013/056720

    申请日：2013-08-27

    Applicant: SIEMENS AKTIENGESELLSCHAFT ,  LEE, Ching-Pang ,  LANDRUM, Evan, C. ,  ZHANG, Jiping

    Inventor： LEE, Ching-Pang ,  LANDRUM, Evan, C. ,  ZHANG, Jiping

    IPC: F01D21/00 ,  F01D25/14 ,  F02C6/08 ,  F02C7/18

    CPC classification number: F01D21/00 ,  F01D25/14 ,  F02C6/08 ,  F02C7/18

    Abstract: During full load operation of gas turbine engine operation, a valve system is maintained in a closed position to substantially prevent air from passing through a piping system of a shell air recirculation system. Upon initiation of a turn down operation, which is implemented to transition the engine to a turning gear state or a shut down state, the valve system is opened to allow air to pass through the piping system. A blower is operated to extract air through at least one outlet port of the shell air recirculation system from an interior volume of an engine casing portion associated with the combustion section, to convey the extracted air through the piping system, and to inject the air into the interior volume of the engine casing portion through at least one inlet port of the shell air recirculation system to circulate air within the engine casing portion.

    Abstract translation: 在燃气轮机发动机运行的全负载运行期间，阀系统保持在关闭位置，以基本上防止空气通过壳体空气再循环系统的管道系统。 在开始执行将发动机转换到转向齿轮状态或关闭状态的转向操作时，阀系统被打开以允许空气通过管道系统。 操作鼓风机以通过壳体空气再循环系统的至少一个出口从与燃烧部分相关联的发动机壳体部分的内部空间提取空气，以将提取的空气输送通过管道系统，并将空气注入 发动机壳体部分的内部容积通过壳体空气再循环系统的至少一个入口端口使发动机壳体部分内的空气循环。

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