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    Temperature detection in a gas turbine
    1.
    发明授权
    Temperature detection in a gas turbine 失效
    燃气轮机中的温度检测

    公开(公告)号：US08334749B1

    公开(公告)日：2012-12-18

    申请号：US12568348

    申请日：2009-09-28

    申请人： Benjamin Lacy ,  Gilbert Kraemer ,  Christian Stevenson

    发明人： Benjamin Lacy ,  Gilbert Kraemer ,  Christian Stevenson

    IPC分类号： H01C7/10

    CPC分类号： F01D17/085 ,  G01K3/10 ,  G01K7/02 ,  G01K7/16 ,  G01K13/02 ,  G01K2205/04

    摘要： A temperature detector includes a first metal and a second metal different from the first metal. The first metal includes a plurality of wires and the second metal includes a wire. The plurality of wires of the first metal are connected to the wire of the second metal in parallel junctions. Another temperature detector includes a plurality of resistance temperature detectors. The plurality of resistance temperature detectors are connected at a plurality of junctions. A method of detecting a temperature change of a component of a turbine includes providing a temperature detector include ing a first metal and a second metal different from the first metal connected to each other at a plurality of junctions in contact with the component; and detecting any voltage change at any junction.

    摘要翻译： 温度检测器包括不同于第一金属的第一金属和第二金属。 第一金属包括多根电线，第二金属包括电线。 第一金属的多根导线以平行结连接到第二金属的导线上。 另一温度检测器包括多个电阻温度检测器。 多个电阻温度检测器以多个连接点连接。 一种检测涡轮机部件的温度变化的方法包括提供温度检测器，该温度检测器包括第一金属和不同于第一金属的第二金属，所述第一金属和第二金属在与所述部件接触的多个接合处彼此连接; 并检测任何接点处的任何电压变化。

    PREMIXED DIRECT INJECTION DISK
    3.
    发明申请
    PREMIXED DIRECT INJECTION DISK 有权
    优先直接注射盘

    公开(公告)号：US20100218501A1

    公开(公告)日：2010-09-02

    申请号：US12394544

    申请日：2009-02-27

    申请人： William David York ,  Willy Steve Ziminsky ,  Thomas Edward Johnson ,  Benjamin Lacy ,  Baifang Zuo ,  Jong Ho Uhm

    发明人： William David York ,  Willy Steve Ziminsky ,  Thomas Edward Johnson ,  Benjamin Lacy ,  Baifang Zuo ,  Jong Ho Uhm

    IPC分类号： F02C7/22

    CPC分类号： F23R3/286 ,  F23D14/02 ,  F23D14/82 ,  F23D2209/10 ,  F23R2900/03282

    摘要： A fuel/air mixing disk for use in a fuel/air mixing combustor assembly is provided. The disk includes a first face, a second face, and at least one fuel plenum disposed therebetween. A plurality of fuel/air mixing tubes extend through the pre-mixing disk, each mixing tube including an outer tube wall extending axially along a tube axis and in fluid communication with the at least one fuel plenum. At least a portion of the plurality of fuel/air mixing tubes further includes at least one fuel injection hole have a fuel injection hole diameter extending through said outer tube wall, the fuel injection hole having an injection angle relative to the tube axis. The invention provides good fuel air mixing with low combustion generated NOx and low flow pressure loss translating to a high gas turbine efficiency, that is durable, and resistant to flame holding and flash back.

    摘要翻译： 提供了一种用于燃料/空气混合燃烧器组件的燃料/空气混合盘。 盘包括第一面，第二面和设置在它们之间的至少一个燃料增压室。 多个燃料/空气混合管延伸穿过预混合盘，每个混合管包括沿管轴线轴向延伸并与至少一个燃料增压室流体连通的外管壁。 多个燃料/空气混合管的至少一部分还包括至少一个燃料喷射孔，其具有延伸穿过所述外管壁的燃料喷射孔直径，燃料喷射孔相对于管轴具有喷射角。 本发明提供了具有低燃烧产生的NOx和低流量压力损失的良好的燃料空气混合，转化为高燃气轮机效率，耐久性，并且耐火焰保持和回闪。

    CURVED FILM COOLING HOLES FOR TURBINE AIRFOIL AND RELATED METHOD
    4.
    发明申请
    CURVED FILM COOLING HOLES FOR TURBINE AIRFOIL AND RELATED METHOD 审中-公开
    用于涡轮机的弯曲膜冷却孔及相关方法

    公开(公告)号：US20120087803A1

    公开(公告)日：2012-04-12

    申请号：US12902517

    申请日：2010-10-12

    申请人： Jesse Blair BUTLER ,  Benjamin LACY

    发明人： Jesse Blair BUTLER ,  Benjamin LACY

    IPC分类号： F01D5/18 ,  B23P15/02

    CPC分类号： F01D5/186 ,  F01D5/187 ,  Y10T29/49341

    摘要： A turbine bucket includes an airfoil portion at one end thereof; a root portion at an opposite end thereof; a platform portion between the airfoil portion and the root portion; at least one internal cavity within or radially inward of the platform portion having at least one film cooling hole extending between the at least one cavity and an external surface of the platform portion. The film cooling hole is curved along a length dimension of the film cooling hole.

    摘要翻译： 涡轮机桶的一端包括翼型部分; 在其相对端的根部; 在翼型部分和根部之间的平台部分; 平台部分内或径向向内的至少一个内部空腔具有至少一个薄膜冷却孔，该薄膜冷却孔在所述至少一个空腔和所述平台部分的外表面之间延伸。 薄膜冷却孔沿薄膜冷却孔的长度尺寸弯曲。

    Premixed direct injection disk
    6.
    发明授权
    Premixed direct injection disk 有权
    预混直接注射盘

    公开(公告)号：US08424311B2

    公开(公告)日：2013-04-23

    申请号：US12394544

    申请日：2009-02-27

    申请人： William David York ,  Willy Steve Ziminsky ,  Thomas Edward Johnson ,  Benjamin Lacy ,  Baifang Zuo ,  Jong Ho Uhm

    发明人： William David York ,  Willy Steve Ziminsky ,  Thomas Edward Johnson ,  Benjamin Lacy ,  Baifang Zuo ,  Jong Ho Uhm

    IPC分类号： F23R3/286

    CPC分类号： F23R3/286 ,  F23D14/02 ,  F23D14/82 ,  F23D2209/10 ,  F23R2900/03282

    摘要： A fuel/air mixing disk for use in a fuel/air mixing combustor assembly is provided. The disk includes a first face, a second face, and at least one fuel plenum disposed therebetween. A plurality of fuel/air mixing tubes extend through the pre-mixing disk, each mixing tube including an outer tube wall extending axially along a tube axis and in fluid communication with the at least one fuel plenum. At least a portion of the plurality of fuel/air mixing tubes further includes at least one fuel injection hole have a fuel injection hole diameter extending through said outer tube wall, the fuel injection hole having an injection angle relative to the tube axis. The invention provides good fuel air mixing with low combustion generated NOx and low flow pressure loss translating to a high gas turbine efficiency, that is durable, and resistant to flame holding and flash back.

    摘要翻译： 提供了一种用于燃料/空气混合燃烧器组件的燃料/空气混合盘。 盘包括第一面，第二面和设置在它们之间的至少一个燃料增压室。 多个燃料/空气混合管延伸穿过预混合盘，每个混合管包括沿管轴线轴向延伸并与至少一个燃料增压室流体连通的外管壁。 多个燃料/空气混合管的至少一部分还包括至少一个燃料喷射孔，其具有延伸穿过所述外管壁的燃料喷射孔直径，燃料喷射孔相对于管轴具有喷射角。 本发明提供了具有低燃烧产生的NOx和低流量压力损失的良好的燃料空气混合，转化为高燃气轮机效率，耐久性，并且耐火焰保持和回闪。