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159 条记录 (耗时 0.052 秒)

    Method for forming turbine seal by cold spray process
    52.
    发明授权
    Method for forming turbine seal by cold spray process 有权
    冷喷涂法形成涡轮密封的方法

    公开(公告)号：US07836591B2

    公开(公告)日：2010-11-23

    申请号：US11082414

    申请日：2005-03-17

    申请人： David B. Allen ,  Ramesh Subramanian

    发明人： David B. Allen ,  Ramesh Subramanian

    IPC分类号： B23P6/00

    CPC分类号： F01D11/02 ,  B23P6/007 ,  F01D5/005 ,  F05D2230/30 ,  F05D2230/80 ,  F05D2230/90 ,  Y10T29/49231 ,  Y10T29/49236 ,  Y10T29/49238 ,  Y10T29/49318

    摘要： A method of forming an interstage seal including removing a diaphragm seal box (14) from a gas turbine compressor assembly (10) and removing a labyrinth sealing member (12) from the diaphragm seal box (14). An abradable material layer (34) may be deposited on the diaphragm seal box (14). A spray gun may be mounted in relation to an engine disk (16) of the gas turbine compressor assembly (10) for cold-spraying a quantity of particles toward the engine disk (16). The particles may be sprayed at a velocity sufficiently high to cause at least a portion of the quantity of particles to adhere to the engine disk (16). The spray gun may be controlled to deposit a quantity of particles on the compressor disk (16) to form a geometry (32) that will abrade the abradable material layer (34) during operation of the gas turbine compressor assembly (10). The geometry (32) abrading the abradable material layer (34) forms an interstage seal. Rotation of the engine disk (16) within the gas turbine compressor assembly (10) may be controlled during the step of controlling the spray gun. The diaphragm seal box (14) may be reinstalled within the gas turbine compressor assembly (10) so that the geometry (32) aligns with the abradable material layer (34).

    摘要翻译： 一种形成级间密封的方法，包括从燃气轮机压缩机组件（10）拆下隔膜密封箱（14），并从隔膜密封箱（14）上拆下迷宫式密封件（12）。 耐磨材料层（34）可以沉积在隔膜密封盒（14）上。 相对于燃气轮机压缩机组件（10）的发动机盘（16）可以安装喷枪，用于将一定数量的颗粒冷却到发动机盘（16）。 颗粒可以以足够高的速度被喷射以使至少一部分颗粒附着到发动机盘（16）上。 可以控制喷枪以将一定数量的颗粒沉积在压缩机盘（16）上以形成在燃气轮机压缩机组件（10）的操作期间磨损可磨损材料层（34）的几何形状（32）。 研磨耐磨材料层（34）的几何形状（32）形成级间密封。 可以在控制喷枪的步骤期间控制发动机盘（16）在燃气涡轮压缩机组件（10）内的旋转。 隔膜密封箱（14）可以重新安装在燃气涡轮压缩机组件（10）内，使得几何形状（32）与可磨损材料层（34）对准。

    Thermal barrier coating having nano scale features
    56.
    发明授权
    Thermal barrier coating having nano scale features 有权
    具有纳米尺度特征的热障涂层

    公开(公告)号：US07413798B2

    公开(公告)日：2008-08-19

    申请号：US10816739

    申请日：2004-04-02

    申请人： Andrew Jeremiah Burns ,  Ramesh Subramanian

    发明人： Andrew Jeremiah Burns ,  Ramesh Subramanian

    IPC分类号： B32B9/00 ,  C23C14/08

    CPC分类号： C23C14/024 ,  C23C14/08 ,  C23C14/083 ,  C23C14/54 ,  C23C28/3215 ,  C23C28/324 ,  C23C28/345 ,  C23C28/3455 ,  G06F19/704 ,  Y10T428/24975 ,  Y10T428/25 ,  Y10T428/252

    摘要： A ceramic thermal barrier coating material (10) containing nano-sized features is predicted to exhibit improved high temperature performance than a comparable material containing fewer of such features. In a coating deposited by an APS process, the nano-sized features may be intersplat columns (32). In a coating deposited by an EB-PVD process, the nano-sized features may be a mixed oxide layer (22) formed of nano-sized mixed oxide particles, or nano-sized alumina projections (24) extending across the interface from the mixed oxide layer into the insulating material layer (20). Alternatively, the nano-sized features may be secondary columnar grains (36) extending laterally from primary columnar grains (34) in a columnar-grained ceramic material.

    摘要翻译： 预期包含纳米尺寸特征的陶瓷热障涂层材料（10）表现出比含有较少这种特征的可比材料更好的高温性能。 在通过APS工艺沉积的涂层中，纳米尺寸特征可以是间隙柱（32）。 在通过EB-PVD工艺沉积的涂层中，纳米尺寸特征可以是由纳米尺寸的混合氧化物颗粒形成的混合氧化物层（22），或者是从混合物的界面延伸的纳米级氧化铝突起（24） 氧化物层进入绝缘材料层（20）。 或者，纳米尺寸特征可以是在柱状晶粒陶瓷材料中从主柱状晶粒（34）横向延伸的第二柱状晶粒（36）。

    Wear monitoring system with embedded conductors
    57.
    发明授权
    Wear monitoring system with embedded conductors 有权
    带嵌入式导体的磨损监测系统

    公开(公告)号：US07270890B2

    公开(公告)日：2007-09-18

    申请号：US11018816

    申请日：2004-12-20

    申请人： Stephen M. Sabol ,  Ramesh Subramanian

    发明人： Stephen M. Sabol ,  Ramesh Subramanian

    IPC分类号： B32B9/00

    CPC分类号： C23C4/18 ,  C23C24/10 ,  F16D66/02 ,  F23M5/00 ,  F23M11/00 ,  F23R3/007 ,  G01N3/56 ,  Y10T428/12611 ,  Y10T428/24273

    摘要： Aspects of the invention relate to a system for monitoring the wear of a component. A conductor can be embedded in the component at a depth from a surface of the component. In one embodiment, the conductor can be operatively connected to a power source to form an electrical circuit. The resistance across the conductor can be measured. As the component contacts a second component, the component can begin to wear. Once the wear progresses to the conductor, changes in the measured resistance can result. Thus, an operator can be alerted that the component has worn to a certain point and that service may be needed. Alternatively, impedance can be measured across the conductor. Because the dielectric permeability of the material surrounding the conductor can affect impedance, changes in impedance can occur as the surface material of the component is worn away.

    摘要翻译： 本发明的方面涉及一种用于监测部件磨损的系统。 导体可以从组件表面的深度嵌入组件中。 在一个实施例中，导体可以可操作地连接到电源以形成电路。 可以测量导体上的电阻。 当组件接触第二组件时，组件可能开始磨损。 一旦磨损进行到导体，可能导致测量的电阻的变化。 因此，可以警告操作者组件已经磨损到某一点并且可能需要该服务。 或者，可以跨导体测量阻抗。 因为导体周围的材料的介电导磁率会影响阻抗，所以当部件的表面材料磨损时，可能会发生阻抗的变化。

    System and computer program product for non-destructive quantification of thermal barrier coating temperatures on service run parts
    59.
    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

    申请人： Ramesh Subramanian ,  Anand Kulkarni

    发明人： Ramesh Subramanian ,  Anand Kulkarni

    IPC分类号： G06F19/00

    CPC分类号： G01N23/046 ,  G01N2223/419 ,  G01N2223/649

    摘要： 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.

    摘要翻译： 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
    60.
    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

    申请人： Anand Kulkarni ,  Christian Campbell ,  Ramesh Subramanian

    发明人： Anand Kulkarni ,  Christian Campbell ,  Ramesh Subramanian

    IPC分类号： B01D50/00

    CPC分类号： F23C13/08 ,  F23C13/00 ,  F23R3/40

    摘要： 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.

    摘要翻译： 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。