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    Method and system for gas temperature measurement
    25.
    发明授权
    Method and system for gas temperature measurement 有权
    气体温度测量方法和系统

    公开(公告)号：US09528880B2

    公开(公告)日：2016-12-27

    申请号：US13969186

    申请日：2013-08-16

    Applicant: General Electric Company

    Inventor： Guanghua Wang ,  Nirm Velumylum Nirmalan ,  Ronald Scott Bunker ,  Todd Garrett Wetzel ,  Robert Michael Zacharias ,  Shawn David Wehe ,  Robert David Briggs

    IPC: G01J5/00 ,  G01K1/14 ,  G01K13/00 ,  G01K3/00 ,  G01J5/10 ,  G01M15/14 ,  G01J5/08 ,  G01J5/60

    CPC classification number: G01J5/10 ,  G01J5/0014 ,  G01J5/0887 ,  G01J5/60 ,  G01M15/14

    Abstract: A temperature measurement system includes a plurality of filaments. The plurality of filaments are configured to emit thermal radiation in a relatively broad and substantially continuous wavelength band at least partially representative of a temperature of the plurality of filaments. A first and second portion of the filaments has a differing first and a second diameter and/or emissivity, respectively. The system also includes a detector array configured to generate electrical signals at least partially representative of the thermal radiation received from the filaments. The system further includes a controller communicatively coupled to the detector array configured to transform the first electrical signals to a first temperature indication at least partially as a function of the first diameter and/or first emissivity and transform the second electrical signals to a second temperature indication at least partially as a function of the second diameter and/or emissivity.

    Abstract translation: 温度测量系统包括多个细丝。 多根细丝构造成发射至少部分代表多个细丝的温度的相对宽且基本上连续的波长带中的热辐射。 长丝的第一和第二部分分别具有不同的第一和第二直径和/或发射率。 该系统还包括检测器阵列，该检测器阵列被配置为产生至少部分代表从灯丝接收的热辐射的电信号。 所述系统还包括通信地耦合到所述检测器阵列的控制器，所述检测器阵列被配置为至少部分地将所述第一电信号转换为第一温度指示作为所述第一直径和/或第一发射率的函数，并将所述第二电信号转换为第二温度指示 至少部分地作为第二直径和/或发射率的函数。

    ENGINE COMPONENT
    26.
    发明申请
    ENGINE COMPONENT 有权
    发动机部件

    公开(公告)号：US20160251967A1

    公开(公告)日：2016-09-01

    申请号：US14633174

    申请日：2015-02-27

    Applicant: General Electric Company

    Inventor： Ronald Scott Bunker

    IPC: F01D5/18

    CPC classification number: F01D5/186 ,  F01D9/065 ,  F05D2240/81 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/50 ,  F23R2900/03042 ,  Y02T50/672 ,  Y02T50/676

    Abstract: An engine component for a gas turbine engine includes a film-cooled substrate having a hot surface facing hot combustion gas flow and a cooling surface facing a cooling fluid flow. A film hole extends through the substrate to an outlet on the hot surface. A flow conditioning structure is provided downstream of the outlet.

    Abstract translation: 用于燃气涡轮发动机的发动机部件包括具有面向热燃烧气流的热表面的薄膜冷却基板和面向冷却流体流的冷却表面。 薄膜孔穿过基底延伸到热表面上的出口。 在出口的下游设有流动调节结构。

    Gas turbine engine and method of operating thereof
    27.
    发明授权
    Gas turbine engine and method of operating thereof 有权
    燃气轮机及其运行方法

    公开(公告)号：US09328663B2

    公开(公告)日：2016-05-03

    申请号：US13906144

    申请日：2013-05-30

    Applicant: General Electric Company

    Inventor： Ronald Scott Bunker

    IPC: F23R3/50 ,  F23R3/18 ,  F23R3/26 ,  F02C6/00 ,  F02C7/08 ,  F02C3/10

    CPC classification number: F02C7/08 ,  F02C3/10 ,  F05D2240/35 ,  F23R3/18 ,  F23R3/26 ,  F23R3/50 ,  F23R2900/00015 ,  F23R2900/03341

    Abstract: A gas turbine engine and method for operating a gas turbine engine includes compressing an air stream in a compressor and generating a post combustion gas by combusting a compressed air stream exiting from the compressor in a combustor. The post combustion gas is expanded in a first turbine. The expanded combustion gas exiting from the first turbine is split into a first stream, a second stream and a third stream. The first stream of the expanded combustion gas is combusted in a reheat combustor. An outer liner and flame stabilizer of the reheat combustor are cooled using the second stream of the expanded combustion gas. An inner liner of the reheat combustor is cooled using the third stream of the expanded combustion gas and a portion of the second stream of the expanded combustion gas passing through the one or more flame stabilizers.

    Abstract translation: 用于操作燃气涡轮发动机的燃气涡轮发动机和方法包括压缩压缩机中的空气流并且通过在燃烧器中燃烧从压缩机排出的压缩空气流而产生后燃气体。 后燃烧气体在第一涡轮机中膨胀。 从第一涡轮机排出的膨胀的燃烧气体被分成第一流，第二流和第三流。 膨胀燃烧气体的第一流在再热燃烧器中燃烧。 使用扩展燃烧气体的第二流冷却再热燃烧器的外衬和火焰稳定器。 再加热燃烧器的内衬层使用膨胀燃烧气体的第三流冷却，并且膨胀的燃烧气体的第二流的一部分通过一个或多个火焰稳定器。

    System and method for removing heat from a turbine
    28.
    发明授权
    System and method for removing heat from a turbine 有权
    从涡轮机去除热量的系统和方法

    公开(公告)号：US09297267B2

    公开(公告)日：2016-03-29

    申请号：US13709306

    申请日：2012-12-10

    Applicant: General Electric Company

    Inventor： Gary Michael Itzel ,  Kevin R. Kirtley ,  Christian Lee Vandervort ,  Ronald Scott Bunker

    IPC: F02G3/00 ,  F01D9/04 ,  F01D5/18 ,  F01D5/28

    CPC classification number: F01D9/041 ,  F01D5/187 ,  F01D5/288 ,  F05D2260/204 ,  F05D2260/205

    Abstract: A system for removing heat from a turbine includes a component in the turbine having a supply plenum and a return plenum therein. A substrate that defines a shape of the component has an inner surface and an outer surface. A coating applied to the outer surface of the substrate has an interior surface facing the outer surface of the substrate and an exterior surface opposed to the interior surface. A first fluid channel is between the outer surface of the substrate and the exterior surface of the coating. A first fluid path is from the supply plenum, through the substrate, and into the first fluid channel, and a second fluid path is from the first fluid channel, through the substrate, and into the return plenum.

    Abstract translation: 用于从涡轮机去除热量的系统包括涡轮机中的部件，其中具有供应气室和回流室。 限定部件形状的基板具有内表面和外表面。 施加到基板的外表面的涂层具有面向基板的外表面的内表面和与内表面相对的外表面。 第一流体通道位于基底的外表面和涂层的外表面之间。 第一流体路径来自供应气室，通过基底，并进入第一流体通道，第二流体路径来自第一流体通道，穿过基底，并进入回流通气室。

    COMPONENTS WITH MICRO COOLED LASER DEPOSITED MATERIAL LAYER AND METHODS OF MANUFACTURE
    29.
    发明申请
    COMPONENTS WITH MICRO COOLED LASER DEPOSITED MATERIAL LAYER AND METHODS OF MANUFACTURE 审中-公开
    微型冷却激光沉积材料层的组成及其制造方法

    公开(公告)号：US20160032766A1

    公开(公告)日：2016-02-04

    申请号：US13826115

    申请日：2013-03-14

    Applicant: General Electric Company

    Inventor： Ronald Scott Bunker ,  William Thomas Carter

    IPC: F01D25/14 ,  F02C7/18 ,  C04B35/653 ,  B23K26/342 ,  B23K26/60

    CPC classification number: F01D25/14 ,  B23K26/34 ,  B23K26/342 ,  B23K26/60 ,  B23K2101/001 ,  B33Y10/00 ,  C04B35/653 ,  C23C4/02 ,  C23C4/073 ,  C23C24/04 ,  C23C24/106 ,  F01D5/288 ,  F02C7/18 ,  F05D2230/10 ,  F05D2230/31 ,  F05D2260/204 ,  Y02T50/672 ,  Y02T50/676

    Abstract: A method of manufacture is provided. The manufacturing method includes using a laser deposition process to apply a laser deposited material on an outer surface of a substrate to form one or more grooves on the outer surface of a substrate. Each groove has a base and an opening and extends at least partially along the outer surface of the substrate, where the substrate has an inner surface that defines at least one hollow, interior space. The manufacturing method further includes disposing an additional material over the laser deposited material, to define one or more channels for cooling the component. The additional material may include additional laser deposited material layers or a coating. Other manufacturing methods and a component are also provided.

    Abstract translation: 提供了一种制造方法。 制造方法包括使用激光沉积工艺将激光沉积材料施加在基板的外表面上，以在基板的外表面上形成一个或多个凹槽。 每个凹槽具有基部和开口，并且至少部分地沿着基底的外表面延伸，其中基底具有限定至少一个中空的内部空间的内表面。 制造方法还包括在激光沉积材料上设置附加材料，以限定用于冷却部件的一个或多个通道。 附加材料可以包括附加的激光沉积材料层或涂层。 还提供了其他制造方法和组件。

    COOLED AIRFOIL TRAILING EDGE AND METHOD OF COOLING THE AIRFOIL TRAILING EDGE
    30.
    发明申请
    COOLED AIRFOIL TRAILING EDGE AND METHOD OF COOLING THE AIRFOIL TRAILING EDGE 有权
    冷却空气涡轮叶片和冷却空气涡轮叶片的方法

    公开(公告)号：US20150147158A1

    公开(公告)日：2015-05-28

    申请号：US14089920

    申请日：2013-11-26

    Applicant: General Electric Company

    Inventor： Guanghua Wang ,  Ronald Scott Bunker ,  Jeremy Clyde Bailey ,  James Peter DeLancey ,  David Benjamin Helmer

    IPC: F01D5/18 ,  F01D9/02

    CPC classification number: F01D5/186 ,  F01D5/187 ,  F01D9/041 ,  F01D9/065 ,  F05D2240/304 ,  F05D2250/13 ,  F05D2250/131 ,  F05D2250/14 ,  F05D2250/141 ,  F05D2250/324 ,  F05D2260/2212 ,  Y02T50/673 ,  Y02T50/676

    Abstract: An airfoil and method of cooling a airfoil including a leading edge, a trailing edge, a suction side, a pressure side and at least one internal cooling channel configured to convey a cooling fluid, is provided. A plurality of trailing edge bleed slots are in fluid communication with the at least one internal cooling channel, wherein a downstream edge of the pressure side of the airfoil lies upstream of a downstream edge of the suction side to expose the plurality of trailing edge bleed slots proximate to the trailing edge of the airfoil. The at least one internal cooling channel is configured to supply the cooling fluid from a source of cooling fluid towards the plurality of trailing edge bleed slots. A plurality of obstruction features are disposed within the at least one internal cooling channel and at a downstream edge of the remaining pressure side. The one or more obstruction features are configured having a predefined substantially polygon shape, to distribute a flow of the cooling fluid and provide distributed cooling to the plurality of trailing edge bleed slots.

    Abstract translation: 提供了一种用于冷却包括前缘，后缘，吸力侧，压力侧和构造成输送冷却流体的至少一个内部冷却通道的翼型的翼型件和方法。 多个后缘排出槽与至少一个内部冷却通道流体连通，其中翼型的压力侧的下游边缘位于吸力侧的下游边缘的上游，以暴露多个后缘排放槽 靠近翼型件的后缘。 至少一个内部冷却通道构造成将冷却流体从冷却流体源向多个后缘排出槽供应。 多个阻塞特征设置在至少一个内部冷却通道内和在剩余压力侧的下游边缘处。 一个或多个障碍物特征被构造成具有预定的基本上多边形的形状，以分配冷却流体的流动并且向多个后缘排放槽提供分布式冷却。

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