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    Thermal barrier coating system with intermetallic overlay bond coat
    1.
    发明授权
    Thermal barrier coating system with intermetallic overlay bond coat 失效
    带有金属间覆盖层的涂层系统

    公开(公告)号：US5238752A

    公开(公告)日：1993-08-24

    申请号：US520017

    申请日：1990-05-07

    申请人： Edward C. Duderstadt ,  Bangalore A. Nagaraj

    发明人： Edward C. Duderstadt ,  Bangalore A. Nagaraj

    IPC分类号： C23C14/02 ,  C23C14/08 ,  C23C28/00

    CPC分类号： C23C28/00 ,  C23C14/025 ,  C23C14/083 ,  Y02T50/67 ,  Y10T428/12549 ,  Y10T428/1259 ,  Y10T428/12611 ,  Y10T428/12618

    摘要： A thermal barrier coating system for high temperature superalloys includes an intermetallic bond coating on the substrate and a ceramic topcoat having a columnar grain structure with the columnar axis perpendicular to the surface of the coating. The intermetallic coating is preferably a nickel aluminide or a platinum aluminide, whose upper surface is oxidized during processing to form a thin layer of predominantly aluminum oxide. The ceramic topcoat is preferably zirconium oxide having from about 6 to 20 percent yttrium oxide.

    摘要翻译： 用于高温超合金的热障涂层系统包括在基底上的金属间粘合涂层和具有柱状晶粒结构的陶瓷面漆，其柱状轴垂直于涂层的表面。 金属间化合物涂层优选为铝化镍或铂铝化合物，其上表面在加工过程中被氧化以形成主要为氧化铝的薄层。 陶瓷面漆优选为具有约6至20％氧化钇的氧化锆。

    High temperature turbine nozzle for temperature reduction by optical reflection and process for manufacturing
    4.
    发明授权
    High temperature turbine nozzle for temperature reduction by optical reflection and process for manufacturing 失效
    用于通过光学反射降温的高温涡轮喷嘴和用于制造的工艺

    公开(公告)号：US06926496B2

    公开(公告)日：2005-08-09

    申请号：US10335486

    申请日：2002-12-31

    申请人： John F. Ackermann ,  Paul V. Arszman ,  Bangalore A. Nagaraj

    发明人： John F. Ackermann ,  Paul V. Arszman ,  Bangalore A. Nagaraj

    IPC分类号： F01D5/28 ,  F01D9/02 ,  F02C7/00 ,  F02K3/10 ,  F23M5/00 ,  F23R3/00 ,  F23R3/18 ,  F23R3/42

    CPC分类号： F23M5/00 ,  F23M2900/05004 ,  F23R3/002 ,  Y02T50/67

    摘要： A high temperature gas turbine component for use in the gas flow path that also is a specular optical reflector. A thin layer of a high temperature reflector is applied to the gas flow path of the component, that is, the surface of the component that forms a boundary for hot combustion gases. The component typically includes a thermal barrier coating overlying the high temperature metallic component that permits the component to operate at elevated temperatures. The thermal barrier coating must be polished in order to provide a surface that can suitably reflect the radiation into the gas flow path. A thin layer of the high temperature reflector the is applied over the polished thermal barrier coating by a process that can adequately adhere the reflector to the polished surface without increasing the roughness of the surface. The high temperature reflector can be applied to any surface aft of the compressor, such as on a turbine nozzle. The surface reflects radiation back into the hot gas flow path. The reflected radiation is not focused onto any other hardware component. The design of the component is such that the radiation is returned to the gas flow path rather than absorbed into a component wall that only serves to increase the temperature of the wall.

    摘要翻译： 用于气体流路的高温燃气轮机部件，其也是镜面光学反射器。 将高温反射器的薄层施加到部件的气体流动路径，即构成热燃烧气体边界的部件的表面。 该部件通常包括覆盖高温金属部件的热障涂层，其允许部件在升高的温度下操作。 必须抛光热障涂层，以便提供可以适当地将辐射反射到气体流动路径中的表面。 通过能够将反射器充分地粘附到抛光表面而不增加表面粗糙度的工艺，将高温反射体的薄层施加在抛光的热障涂层上。 高温反射器可以应用于压缩机后面的任何表面，例如在涡轮喷嘴上。 该表面将辐射反射回热气流路径。 反射的辐射没有集中在任何其他硬件组件上。 部件的设计使得辐射返回到气体流动路径而不是被吸收到仅用于增加壁的温度的部件壁中。

    Method for improving the performance of oxidizable ceramic materials in oxidizing environments
    5.
    发明授权
    Method for improving the performance of oxidizable ceramic materials in oxidizing environments 失效
    在氧化环境中提高可氧化陶瓷材料性能的方法

    公开(公告)号：US06485791B1

    公开(公告)日：2002-11-26

    申请号：US09544041

    申请日：2000-04-06

    申请人： Bangalore A. Nagaraj

    发明人： Bangalore A. Nagaraj

    IPC分类号： C23C1430

    CPC分类号： C04B41/009 ,  C04B41/52 ,  C04B41/89 ,  C23C28/04 ,  C04B41/4529 ,  C04B41/5035 ,  C04B41/53 ,  C04B41/5031 ,  C04B41/522 ,  C04B41/0072 ,  C04B41/5037 ,  C04B41/5042 ,  C04B35/565 ,  C04B35/584 ,  C04B35/806

    摘要： Improved adhesion of thermal barrier coatings to nonmetallic substrates using a dense layer of ceramic on an underlying nonmetallic substrate that includes at least one oxidizable component. The improved adhesion occurs because the application of the dense ceramic layer forms a diffusion barrier for oxygen. This diffusion barrier prevents the oxidizable component of the substrate from decomposing. The present invention applies ceramic by a process that deposits a relatively thick and dense ceramic layer on the underlying substrate. The formation of the dense layer of ceramic avoids the problem of void formation associated with ceramic formation by most prior art thermal decomposition processes. The formation of voids has been associated with premature spalling of thermal barrier layers and other protective layers applied to substrates.

    摘要翻译： 使用包含至少一种可氧化组分的下层非金属基底上的致密陶瓷层来改善热障涂层对非金属基底的粘合性。 由于应用致密的陶瓷层形成氧的扩散阻挡层，所以发生改善的粘附。 该扩散阻挡层防止基底的可氧化成分分解。 本发明通过在下面的衬底上沉积相对厚且致密的陶瓷层的方法来应用陶瓷。 通过大多数现有技术的热分解过程，陶瓷致密层的形成避免了与陶瓷形成相关的空隙形成的问题。 空隙的形成已经与施加到基底上的热障层和其它保护层的过早剥落有关。

    Coated turbine component and its fabrication
    6.
    发明授权
    Coated turbine component and its fabrication 有权
    涂层涡轮机组件及其制造

    公开(公告)号：US06283715B1

    公开(公告)日：2001-09-04

    申请号：US09405479

    申请日：1999-09-24

    申请人： Bangalore A. Nagaraj ,  Norbert O. Maurer ,  Eric A. Estill ,  Elissa H. Lee

    发明人： Bangalore A. Nagaraj ,  Norbert O. Maurer ,  Eric A. Estill ,  Elissa H. Lee

    IPC分类号： F01D514

    CPC分类号： C23C28/3215 ,  C23C4/00 ,  C23C28/321 ,  C23C28/325 ,  C23C28/34 ,  C23C28/3455 ,  F01D5/288 ,  Y02T50/67 ,  Y02T50/673

    摘要： A gas turbine component has a platform, a shank extending downwardly from the platform, and an airfoil extending upwardly from the platform. The gas turbine component is coated by first applying a first chromide layer overlying the base metal of at least a portion of the shank and interdiffused therewith, and second applying a second coating on at least a portion of the airfoil. The second coating optionally includes a second chromide layer contacting the base metal of the airfoil and interdiffused therewith, and includes an aluminide protective layer overlying the second chromide layer. The first chromide layer on the shank and the second chromide layer on the airfoil may be within the same chromium composition range (for example, from about 20 to about 30 weight percent chromium) and thickness range (for example, from about 0.001 to about 0.002 inch), and deposited at the same time.

    摘要翻译： 燃气轮机部件具有平台，从平台向下延伸的柄部以及从平台向上延伸的翼型件。 通过首先施加覆盖柄的至少一部分的基底金属并与其相互扩散的第一铬化物层，并且在翼型的至少一部分上施加第二涂层来涂覆燃气轮机部件。 第二涂层任选地包括与翼型件的母材接触并与其相互扩散的第二铬化物层，并且包括覆盖在第二铬化物层上的铝化物保护层。 刀柄上的第一铬化物层和翼型上的第二铬化物层可以在相同的铬组成范围内（例如，约20至约30重量％的铬）和厚度范围（例如，约0.001至约0.002 英寸），并同时沉积。

    Method for repairing a thermal barrier coating
    7.
    发明授权
    Method for repairing a thermal barrier coating 失效
    修补热障涂层的方法

    公开(公告)号：US5723078A

    公开(公告)日：1998-03-03

    申请号：US651183

    申请日：1996-05-24

    申请人： Bangalore A. Nagaraj ,  Seetharamaiah Mannava ,  Bhupendra K. Gupta

    发明人： Bangalore A. Nagaraj ,  Seetharamaiah Mannava ,  Bhupendra K. Gupta

    IPC分类号： C23C4/00 ,  C23C4/02 ,  C23C14/04 ,  B32B35/00 ,  B23P6/00

    CPC分类号： C23C4/00 ,  C23C14/046 ,  C23C4/02 ,  F01D5/005 ,  F01D5/288 ,  F05D2230/313 ,  Y10T29/49728 ,  Y10T29/49746 ,  Y10T428/20

    摘要： A method of repairing a thermal barrier coating on an article designed for use in a hostile thermal environment, such as turbine, combustor and augmentor components of a gas turbine engine. The method is particularly suited for the repair of thermal barrier coatings composed of a metallic bond layer formed on the surface of the article, and a columnar ceramic layer overlaying the bond layer. The method entails the steps of cleaning the bond layer exposed by localized spallation, treating the bond layer so as to texture its exposed surface, and then depositing a ceramic material on the surface of the bond layer so as to form a ceramic repair layer that completely covers the bond layer. Deposition of the repair layer can be carried out such that its upper surface projects above the adjacent ceramic layer, followed by abrading the repair layer to a height substantially level with the ceramic layer.

    摘要翻译： 修复设计用于恶劣热环境（例如燃气涡轮发动机的涡轮机，燃烧器和增压器部件）的制品上的热障涂层的方法。 该方法特别适用于由形成在制品表面上的金属结合层和覆盖接合层的柱状陶瓷层组成的热障涂层的修复。 该方法需要清洁通过局部剥离暴露的接合层的步骤，处理接合层以便将其暴露的表面织构，然后在接合层的表面上沉积陶瓷材料，以形成完全 覆盖了粘结层。 可以进行修复层的沉积，使得其上表面突出在相邻陶瓷层上方，然后将修复层研磨至与陶瓷层基本一致的高度。

    CORROSION COATING FOR TURBINE BLADE ENVIRONMENTAL PROTECTION
    10.
    发明申请
    CORROSION COATING FOR TURBINE BLADE ENVIRONMENTAL PROTECTION 有权
    用于涡轮叶片环境保护的腐蚀涂层

    公开(公告)号：US20100040476A1

    公开(公告)日：2010-02-18

    申请号：US11968368

    申请日：2008-01-02

    申请人： Bangalore A. Nagaraj ,  Mark D. Gorman

    发明人： Bangalore A. Nagaraj ,  Mark D. Gorman

    IPC分类号： F01D5/28

    CPC分类号： C23C10/04 ,  C23C10/18 ,  C23C10/26 ,  C23C10/28 ,  C23C10/52 ,  C23C10/60 ,  F01D5/288 ,  Y10T428/12931

    摘要： A gas turbine engine turbine blade comprising an airfoil section, a platform section, an under platform section, and a dovetail section, an exterior surface of the dovetail section comprising a shank exterior surface and a serrated exterior surface. The blade further comprises a silicon-modified diffusion aluminide layer a surface of a turbine blade section selected from the group consisting of an exterior surface of the under platform section, the exterior surface of the dovetail section, and combinations thereof, the silicon modified diffusion aluminide layer having a concentration of silicon at a surface of the silicon-modified diffusion aluminide layer in the range of about 1 weight percent to about 10 weight percent and a concentration of aluminum at the surface of the silicon modified diffusion aluminide layer in the range of about 5 weight percent to about 25 weight percent.

    摘要翻译： 一种燃气涡轮发动机涡轮叶片，包括翼型部分，平台部分，下平台部分和燕尾部分，燕尾部分的外表面包括柄外表面和锯齿形外表面。 叶片还包括硅改性的扩散铝化物层，涡轮叶片部分的表面，其选自下部平台部分的外表面，燕尾部分的外表面及其组合，硅改性扩散铝化物 在硅改性扩散铝化物层的表面具有约1重量％至约10重量％的范围内的具有硅浓度的层，并且在硅改性扩散铝化物层的表面处的铝的浓度在约 5重量％至约25重量％。