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    Methodologies for non-destructive quantification of thermal barrier coating temperatures on service run parts
    1.
    发明申请
    Methodologies for non-destructive quantification of thermal barrier coating temperatures on service run parts 有权

    公开(公告)号：US20070076845A1

    公开(公告)日：2007-04-05

    申请号：US11243370

    申请日：2005-10-04

    Applicant: Ramesh Subramanian ,  Anand Kulkarni

    Inventor： Ramesh Subramanian ,  Anand Kulkarni

    IPC: G01B15/06 ,  G01N23/02

    CPC classification number: G01N23/046 ,  G01N2223/419

    Abstract: Methodologies for non-destructively inspecting and characterizing micro-structural features in a thermal barrier coating (TBC) on a component, wherein the micro-structural features define pores and cracks, if any, in the TBC. The micro-structural features having characteristics at least in part based on a type of process used for developing the TBC and affected by operational thermal loads to which a TBC is exposed. In one embodiment, the method allows detecting micro-structural features in a TBC, wherein the detecting of the micro-structural features is based on energy transmitted through the TBC, such as may be performed with a micro-feature detection system 20. The transmitted energy is processed to generate data representative of the micro-structural features, such as may be generated by a controller 26. The data representative of the micro-structural features is processed (e.g., by a processor 30) to determine at least one of the following: volumetric porosity information for the TBC and variation in the characteristics of the micro-structural features over a thickness of the TBC. Based on the results of the data processing, information is generated regarding at least one of the following: a present condition of the thermal barrier coating and a future likely condition of the thermal barrier coating. In another embodiment, one can estimate a level of thermal load to which the thermal barrier coating has been exposed.

    System and computer program product for non-destructive quantification of thermal barrier coating temperatures on service run parts
    2.
    发明申请
    System and computer program product for non-destructive quantification of thermal barrier coating temperatures on service run parts 有权
    系统和计算机程序产品，可在服务运行部件上对热障涂层温度进行非破坏性定量

    公开(公告)号：US20070078609A1

    公开(公告)日：2007-04-05

    申请号：US11242664

    申请日：2005-10-04

    Applicant: Ramesh Subramanian ,  Anand Kulkarni

    Inventor： Ramesh Subramanian ,  Anand Kulkarni

    IPC: G06F19/00

    CPC classification number: G01N23/046 ,  G01N2223/419 ,  G01N2223/649

    Abstract: System and computer program product for non-destructively inspecting and characterizing micro-structural features in a thermal barrier coating (TBC) on a component, wherein the micro-structural features define pores and cracks, if any, in the TBC. The micro-structural features having characteristics at least in part based on a type of process used for developing the TBC and affected by operational thermal loads to which a TBC is exposed. In one embodiment, the method allows detecting micro-structural features in a TBC, wherein the detecting of the micro-structural features is based on energy transmitted through the TBC, such as may be performed with a micro-feature detection system 20. The transmitted energy is processed to generate data representative of the micro-structural features, such as may be generated by a controller 26. The data representative of the micro-structural features is processed (e.g., by a processor 30) to determine at least one of the following: volumetric porosity information for the TBC and variation in the characteristics of the micro-structural features over a thickness of the TBC. Based on the results of the data processing, information is generated regarding at least one of the following: a present condition of the thermal barrier coating and a future likely condition of the thermal barrier coating. In another embodiment, one can estimate a level of thermal load to which the thermal barrier coating has been exposed.

    Abstract translation: 系统和计算机程序产品，用于对部件中的热障涂层（TBC）进行非破坏性检查和表征微结构特征，其中微结构特征限定了TBC中的孔隙和裂纹（如果有的话）。 所述微结构特征至少部分地基于用于显影TBC并受TBC暴露于的​​操作热负荷影响的过程的类型的特征。 在一个实施例中，该方法允许检测TBC中的微结构特征，其中微结构特征的检测基于通过TBC传输的能量，诸如可以用微特征检测系统20执行。 处理发送的能量以产生表示微结构特征的数据，诸如可由控制器26产生。 代表微结构特征的数据被处理（例如，由处理器30），以确定以下中的至少一个：TBC的体积孔隙度信息和微结构特征在特征厚度方面的变化 TBC。 基于数据处理的结果，产生关于以下中的至少一个的信息：热障涂层的现状和热障涂层的将来可能的状态。 在另一个实施例中，可以估计已经暴露了热障涂层的热负荷水平。

    Catalytic thermal barrier coatings
    3.
    发明申请
    Catalytic thermal barrier coatings 有权
    催化热障涂层

    公开(公告)号：US20060245984A1

    公开(公告)日：2006-11-02

    申请号：US11244739

    申请日：2005-10-06

    Applicant: Anand Kulkarni ,  Christian Campbell ,  Ramesh Subramanian

    Inventor： Anand Kulkarni ,  Christian Campbell ,  Ramesh Subramanian

    IPC: B01D50/00

    CPC classification number: F23C13/08 ,  F23C13/00 ,  F23R3/40

    Abstract: A catalyst element (30) for high temperature applications such as a gas turbine engine. The catalyst element includes a metal substrate such as a tube (32) having a layer of ceramic thermal barrier coating material (34) disposed on the substrate for thermally insulating the metal substrate from a high temperature fuel/air mixture. The ceramic thermal barrier coating material is formed of a crystal structure populated with base elements but with selected sites of the crystal structure being populated by substitute ions selected to allow the ceramic thermal barrier coating material to catalytically react the fuel-air mixture at a higher rate than would the base compound without the ionic substitutions. Precious metal crystallites may be disposed within the crystal structure to allow the ceramic thermal barrier coating material to catalytically react the fuel-air mixture at a lower light-off temperature than would the ceramic thermal barrier coating material without the precious metal crystallites.

    Abstract translation: 一种用于高温应用的催化剂元件（30），例如燃气涡轮发动机。 催化剂元件包括金属基底，例如具有设置在基底上的陶瓷热障涂层材料层（34）的管（32），用于将金属基底与高温燃料/空气混合物进行绝热。 陶瓷热障涂层材料由填充有基底元件的晶体结构形成，但是晶体结构的选定位置由选择的替代离子填充以允许陶瓷热障涂层材料以更高的速率催化反应燃料 - 空气混合物 比没有离子取代基础化合物。 贵金属微晶可以设置在晶体结构内，以允许陶瓷热障涂层材料在比没有贵金属微晶的陶瓷热障涂层材料低的关闭温度下催化反应燃料 - 空气混合物。

    Apparatus and method of detecting wear in an abradable coating system
    4.
    发明申请
    Apparatus and method of detecting wear in an abradable coating system 有权
    在可磨损涂层系统中检测磨损的装置和方法

    公开(公告)号：US20060056960A1

    公开(公告)日：2006-03-16

    申请号：US11269044

    申请日：2005-11-08

    Applicant: Stephen Sabol ,  Ramesh Subramanian ,  Anand Kulkarni

    Inventor： Stephen Sabol ,  Ramesh Subramanian ,  Anand Kulkarni

    IPC: F04D29/00

    CPC classification number: C23C4/18 ,  B33Y80/00 ,  C23C24/04 ,  C23C28/3215 ,  C23C28/3455 ,  F01D17/02 ,  F01D17/08 ,  F01D21/003 ,  F01D21/04 ,  F01D25/24 ,  F04D27/001 ,  F04D29/324 ,  F04D29/526 ,  F04D29/542 ,  F05D2230/30 ,  F05D2230/90 ,  F05D2260/80 ,  F23M5/00 ,  F23M11/00 ,  F23R3/007 ,  G01K7/028 ,  G01K13/02 ,  G01K17/20 ,  G01K2205/04 ,  G01N3/56 ,  Y10T428/24926

    Abstract: A component for use in a combustion turbine (10) is provided that includes a substrate (212) and an abradable coating system (216) deposited on the substrate (212). A planar proximity sensor (250) may be deposited beneath a surface of the abradable coating system (216) having circuitry (252) configured to detect intrusion of an object (282) into the abradable coating system (216). A least one connector (52) may be provided in electrical communication with the planar proximity sensor (250) for routing a data signal from the planar proximity sensor (250) to a termination location (59). A plurality of trenches (142) may be formed at respective different depths below the surface of the abradable coating system (216) with a planar proximity sensor (250) deposited within each of the plurality of trenches (142). A processing module (34) may be programmed for receiving data from the planar proximity sensor (250) and calculating a clearance between a row of blades (18,19) within a combustion turbine and the planar proximity sensor (250). The processing module (34) may control a clearance between the row of blades (18) and a ring segment (284) based on data received from the planar proximity sensors (250).

    Abstract translation: 提供了一种用于燃气轮机（10）的部件，其包括沉积在基板（212）上的基板（212）和可磨损涂层系统（216）。 平面接近传感器（250）可以沉积在具有电路（252）的可磨损涂层系统（216）的表面下方，该电路被构造成检测物体（282）侵入到可磨损涂层系统（216）中。 可以提供与平面接近传感器（250）电通信的至少一个连接器（52），用于将数据信号从平面接近传感器（250）路由到终止位置（59）。 可以在沉积在多个沟槽（142）的每一个内的平面接近传感器（250）在可磨损涂层系统（216）的表面下方的相应不同深度处形成多个沟槽（142）。 处理模块（34）可以被编程为从平面接近传感器（250）接收数据并且计算燃烧涡轮机内的一排叶片（18,19）与平面接近传感器（250）之间的间隙。 处理模块（34）可以基于从平面接近传感器（250）接收的数据来控制叶片行（18）和环形段（284）之间的间隙。

    Ceramic wash-coat for catalyst support
    5.
    发明申请
    Ceramic wash-coat for catalyst support 有权
    用于催化剂载体的陶瓷洗涂层

    公开(公告)号：US20070161507A1

    公开(公告)日：2007-07-12

    申请号：US11330555

    申请日：2006-01-12

    Applicant: Anand Kulkarni ,  Ramesh Subramanian ,  Stephen Sabol

    Inventor： Anand Kulkarni ,  Ramesh Subramanian ,  Stephen Sabol

    IPC: B01J23/10

    CPC classification number: B01J23/002 ,  B01J23/10 ,  B01J23/63 ,  B01J37/0242 ,  B01J37/0248 ,  B01J2523/00 ,  F23C13/08 ,  B01J2523/31 ,  B01J2523/47 ,  B01J2523/824 ,  B01J2523/41 ,  B01J2523/3706 ,  B01J2523/3725 ,  B01J2523/22 ,  B01J2523/48

    Abstract: A wash-coat (16) for use as a support for an active catalyst species (18) and a catalytic combustor component (10) incorporating such wash-coat. The wash-coat is a solid solution of alumina or alumina-based material (Al2O3-0-3 wt % La2O3) and a further oxide exhibiting a coefficient of thermal expansion that is lower than that exhibited by alumina. The further oxide may be silicon dioxide (2-30 wt % SiO2), zirconia silicate (2-30 wt % ZrSiO4), neodymium oxide (0-4 wt %), titania (Al2O3-3-40% TiO2) or alumina-based magnesium aluminate spinel (Al2O3-25 wt % MgO) in various embodiments. The active catalyst species may be palladium and a second metal in a concentration of 10-50% of the concentration of the palladium.

    Abstract translation: 用作活性催化剂种类（18）和催化燃烧器组分（10）的载体的洗涂层（16），其结合有这种洗衣层。 洗涤涂层是氧化铝或氧化铝基材料（Al 2 O 3 - 3重量％La 2 O 3）的固溶体 3）和另外表现出比氧化铝表现出的热膨胀系数低的氧化物。 另外的氧化物可以是二氧化硅（2-30重量％SiO 2），氧化锆硅酸盐（2-30重量％ZrSiO 4+），氧化钕（0-4重量％ ％），二氧化钛（Al 2 O 3 3→3％％TiO 2）或氧化铝基铝酸镁尖晶石（Al 2 O 3） 2 O 3 -25％（重量）MgO）。 活性催化剂种类可以是钯，浓度为钯浓度的10-50％的第二种金属。

    Apparatus and method of monitoring operating parameters of a gas turbine
    6.
    发明申请
    Apparatus and method of monitoring operating parameters of a gas turbine 有权
    监测燃气轮机运行参数的装置和方法

    公开(公告)号：US20060056959A1

    公开(公告)日：2006-03-16

    申请号：US11269043

    申请日：2005-11-08

    Applicant: Stephen Sabol ,  Ramesh Subramanian ,  Anand Kulkarni

    Inventor： Stephen Sabol ,  Ramesh Subramanian ,  Anand Kulkarni

    IPC: F04D29/00

    CPC classification number: F01D17/02 ,  B33Y80/00 ,  F01D17/08 ,  F01D21/003 ,  F05D2230/30 ,  F05D2230/90 ,  F05D2260/80

    Abstract: A component for use in a combustion turbine (10) is provided that includes a substrate (212) and a microelectromechanical system (MEMS) device (50, 250) affixed to the substrate (212). At least one connector (52) may be deposited in electrical communication with the MEMS device (50, 250) for routing a data signal from the MEMS device (50, 250) to a termination location (59). A barrier coating (216) may be deposited on the substrate (212) wherein the MEMS device (50, 250) is affixed beneath a surface of the barrier coating (216). A plurality of trenches (142) may be formed in the barrier coating (216) at respective different depths below the surface of the barrier coating (216) and a MEMS device (50, 250) deposited within each of the plurality of trenches (142). A monitoring system (30) is provided that may include a processing module (34) programmed for receiving data from the MEMS device (50, 250).

    Abstract translation: 提供了一种用于燃气轮机（10）的部件，其包括固定到基板（212）上的基板（212）和微机电系统（MEMS）装置（50,250）。 至少一个连接器（52）可以沉积成与MEMS器件（50,250）电连通，用于将来自MEMS器件（50,250）的数据信号路由到终止位置（59）。 阻挡涂层（216）可以沉积在衬底（212）上，其中MEMS器件（50,250）被固定在阻挡涂层（216）的表面下方。 多个沟槽（142）可以在阻挡涂层（216）的表面下方的相应不同深度处形成在阻挡涂层（216）中，以及沉积在多个沟槽（142）的每一个内的MEMS装置（50,250） ）。 提供了一种监视系统（30），其可包括被编程用于从MEMS装置（50,250）接收数据的处理模块（34）。

    Instrumented component for wireless telemetry
    8.
    发明授权
    Instrumented component for wireless telemetry 有权
    无线遥测仪表组件

    公开(公告)号：US08797179B2

    公开(公告)日：2014-08-05

    申请号：US13015765

    申请日：2011-01-28

    Applicant: Ramesh Subramanian ,  Anand A. Kulkarni ,  David J. Mitchell ,  Bjoern Karlsson ,  Rod Waits ,  John R. Fraley

    Inventor： Ramesh Subramanian ,  Anand A. Kulkarni ,  David J. Mitchell ,  Bjoern Karlsson ,  Rod Waits ,  John R. Fraley

    IPC: G08C19/16 ,  G08C19/22 ,  H04Q9/00

    CPC classification number: H04Q9/00 ,  F23N2023/38 ,  F23N2031/10 ,  F23R3/00 ,  G01D5/48 ,  H01F38/14 ,  H01F38/18 ,  H04Q2209/40 ,  H04Q2209/886

    Abstract: A telemetry system for use in a combustion turbine engine (10) that includes a first sensor (306) in connection with a turbine blade (301) or vane (22). A first telemetry transmitter circuit (312) is affixed to the turbine blade and routes electronic data signals, indicative of a condition of the blade, from the sensor to a rotating data antenna (314) that is affixed to the turbine blade or is on a same substrate as that of the circuit. A stationary data antenna (333) may be affixed to a stationary component (323) proximate and in spaced relation to the rotating data antenna for receiving electronic data signals from the rotating data antenna. A second sensor (335) transmits electronic data signals indicative of the stationary component to a second telemetry circuit (332), which routes the signals to the stationary antenna. The stationary antenna transmits the electronic data signals to a receiver (338).

    Abstract translation: 一种用于燃气涡轮发动机（10）的遥测系统，其包括与涡轮叶片（301）或叶片（22）连接的第一传感器（306）。 第一遥测发射器电路（312）被固定到涡轮机叶片并且将表示叶片的状态的电子数据信号从传感器传送到固定到涡轮叶片上的旋转数据天线（314） 与电路相同的衬底。 固定数据天线（333）可以固定到与旋转数据天线接近且间隔开的固定部件（323），用于从旋转数据天线接收电子数据信号。 第二传感器（335）将指示静止分量的电子数据信号发送到第二遥测电路（332），其将信号路由到固定天线。 固定天线将电子数据信号发送到接收器（338）。

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