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    High-emissivity infrared coating applications for use in hirss applications
    2.
    发明申请
    High-emissivity infrared coating applications for use in hirss applications 有权
    高辐射红外线涂层应用用于hirss应用

    公开(公告)号：US20060086077A1

    公开(公告)日：2006-04-27

    申请号：US10972552

    申请日：2004-10-25

    申请人： Andrew Skoog ,  Jane Murphy ,  John Jasany ,  Aaron Gastrich ,  Timothy Manning

    发明人： Andrew Skoog ,  Jane Murphy ,  John Jasany ,  Aaron Gastrich ,  Timothy Manning

    IPC分类号： F02C7/00

    CPC分类号： F02K1/825 ,  C23C4/02 ,  C23C24/08 ,  C23C28/042 ,  C23C28/321 ,  C23C28/345 ,  C23C28/3455 ,  C23C30/00 ,  F01D5/288 ,  F05D2230/90 ,  F05D2300/2102 ,  F05D2300/611 ,  Y02T50/67 ,  Y02T50/671

    摘要： A high emissivity (Hi-E) coating for use on the exhaust baffles of HIRSS systems. HIRSS systems were developed to reduce the infrared (IR) signature of helicopter engines. Increasing operating temperatures of helicopter engines have made the HIRSS systems less effective. An infrared coating applied over selected portions of the HIRSS reduces the IR of the system. The Hi-E coating comprises, in weight percent, 30-80% refractory oxide pigment, 5-20% binder, 1-15% potassium oxide, optionally up to about 15% glass-forming material and the balance refractory oxide powder. When applied to provide a surface finish of 1100Ra microinches or coarser, the coated HIRSS has a significantly reduced hemispherical reflectance in the IR frequency range.

    摘要翻译： 用于HIRSS系统排气挡板的高发射率（Hi-E）涂层。 开发了HIRSS系统来减少直升机发动机的红外（IR）签名。 增加直升机发动机的运行温度使得HIRSS系统的效率降低。 在HIRSS的选定部分施加的红外涂层减少了系统的IR。 Hi-E涂层以重量％计含有30-80％的难熔氧化物颜料，5-20％的粘合剂，1-15％的氧化钾，任选的最多约15％的玻璃形成材料和余量的难熔氧化物粉末。 当应用于提供1100Ra / a或更大的表面光洁度时，涂覆的HIRSS在IR频率范围内具有显着降低的半球反射。

    Method of applying an optical coating to an article surface
    4.
    发明申请
    Method of applying an optical coating to an article surface 失效
    将光学涂层施加到制品表面的方法

    公开(公告)号：US20050079284A1

    公开(公告)日：2005-04-14

    申请号：US10681676

    申请日：2003-10-08

    申请人： Daniel Ivkovich ,  Andrew Skoog ,  Jane Murphy ,  Thomas Rentz ,  William Stowell ,  Bryan Bojanowski

    发明人： Daniel Ivkovich ,  Andrew Skoog ,  Jane Murphy ,  Thomas Rentz ,  William Stowell ,  Bryan Bojanowski

    IPC分类号： C23C14/00 ,  C23C26/00 ,  C23C28/00 ,  G02B1/10 ,  B29D11/00

    CPC分类号： G02B1/10 ,  C23C14/0005 ,  C23C26/00 ,  Y02T50/67 ,  Y10T156/1116

    摘要： An optical coating is applied to an article surface of an article by applying a first release system to a deposition substrate, and depositing the optical coating onto the deposition substrate. A second release system and transfer substrate is applied to the second face of the optical coating. The first release system is dissolvable in a first-release-coating solvent that does not dissolve the second release system. The first release system is dissolved in the first-release-coating solvent that does not dissolve the second release system, to separate the optical coating from the deposition substrate. The first face of the optical coating is affixed to the article surface, and the transfer substrate is separated from the optical coating. Any of a variety of affixing techniques may be used.

    摘要翻译： 通过将第一释放系统施加到沉积衬底上并将光学涂层沉积到沉积衬底上，将光学涂层施加到制品的制品表面。 将第二释放系统和转印衬底施加到光学涂层的第二面。 第一释放系统可溶解在不溶解第二释放系统的第一释放 - 涂层溶剂中。 将第一释放系统溶解在不溶解第二释放系统的第一释放 - 涂层溶剂中，以将光学涂层与沉积基材分离。 将光学涂层的第一面固定在物品表面上，并将转印基板与光学涂层分离。 可以使用各种固定技术中的任何一种。

    Field repairable high temperature smooth wear coating
    6.
    发明申请
    Field repairable high temperature smooth wear coating 有权
    现场可修高温平滑磨损涂层

    公开(公告)号：US20050228098A1

    公开(公告)日：2005-10-13

    申请号：US10819856

    申请日：2004-04-07

    申请人： Andrew Skoog ,  Jane Murphy ,  William Stowell ,  David Caldwell

    发明人： Andrew Skoog ,  Jane Murphy ,  William Stowell ,  David Caldwell

    IPC分类号： B05D7/14 ,  C23C24/08 ,  C23C26/00 ,  C08K3/18

    CPC分类号： C23C28/3215 ,  C23C24/08 ,  C23C28/321 ,  C23C28/325 ,  C23C28/345 ,  C23C28/3455 ,  C23C28/347 ,  Y02T50/67

    摘要： A chemical composition and method for repairing a thermal barrier coating on a component designed for use in a hostile thermal environment, such as turbine, combustor and augmentor components of a gas turbine engine. The method repairs a thermal barrier coating on a component that has suffered localized damage to the thermal barrier coating. After cleaning the surface area of the component exposed by the localized spallation, a paste-like mixture of a ceramic composition comprising ceramic powders and nano-sized ceramic materials in a binder is applied to the surface area of the component, and is optionally smoothed using mechanical means. The composition is then allowed to dry and cure to form a dried coating having polymeric characteristics. Upon subsequent heating, the dried coating reacts to produce a glassy ceramic repair coating. Due to the thixotropic properties of the coating composition upon application to a component, the repair method can be performed in-situ while the component remains installed in its operating environment.

    摘要翻译： 用于修复设计用于恶劣热环境的部件上的热障涂层的化学组成和方法，例如燃气涡轮发动机的涡轮机，燃烧器和增压器部件。 该方法修复已经对热障涂层局部损坏的部件上的热障涂层。 在清洁通过局部剥离暴露的部件的表面积之后，将包含陶瓷粉末和纳米尺寸陶瓷材料的陶瓷组合物的粘合剂的糊状混合物施加到部件的表面区域，并且可选地使用 机械手段。 然后将组合物干燥并固化以形成具有聚合特性的干燥涂层。 随后加热，干燥的涂层反应生成玻璃状陶瓷修补涂层。 由于涂料组合物在施用于组分时的触变性能，可以在组分保持安装在其操作环境中时原位进行修复方法。

    Electrostatic spray for coating aircraft engine components
    7.
    发明申请
    Electrostatic spray for coating aircraft engine components 审中-公开
    用于喷涂飞机发动机部件的静电喷雾

    公开(公告)号：US20070104886A1

    公开(公告)日：2007-05-10

    申请号：US11272167

    申请日：2005-11-10

    申请人： Matthew Buczek ,  Andrew Skoog ,  Mark Rechtsteiner ,  Jane Murphy

    发明人： Matthew Buczek ,  Andrew Skoog ,  Mark Rechtsteiner ,  Jane Murphy

    IPC分类号： H05C1/00 ,  B05D1/04

    CPC分类号： C23C24/00 ,  B05B5/032 ,  B05B5/1683 ,  B05B14/48 ,  C23C4/12 ,  C23C4/18 ,  Y02T50/67 ,  Y02T50/6765

    摘要： Electrostatic deposition of high performance powdered materials onto gas turbine surfaces. The process also includes post-deposition thermal staging of the deposited powder to provide a durable coating that will satisfy the demands of turbine engine operation. The process envisions application of organic-based powdered materials, glass/ceramic powdered materials and metal-based powdered materials and combinations thereof using electrostatic techniques to components exposed to low temperature operations, such as may be found in the front section of a gas turbine engine or to the exterior portions of an aircraft engine, and metal-containing glass ceramics, glass-ceramic materials, or materials that can be transformed into glass ceramic materials, when applied to components exposed to high temperature operations, such as may be found in the turbine and exhaust sections of a gas turbine engine or the flaps of an aircraft.

    摘要翻译： 将高性能粉末材料静电沉积到燃气轮机表面上。 该方法还包括沉积粉末的沉积后分级，以提供将满足涡轮发动机运行需求的耐用涂层。 该方法设想使用静电技术将有机基粉末材料，玻璃/陶瓷粉末材料和金属基粉末材料及其组合应用于暴露于低温操作的部件，例如可以在燃气涡轮发动机的前部 或飞机发动机的外部部分，以及金属玻璃陶瓷，玻璃陶瓷材料或可转化成玻璃陶瓷材料的材料，当应用于暴露于高温操作的部件时，例如可以在 燃气涡轮发动机的涡轮机和排气段或飞行器的翼片。

    Method for forming ceramic layer
    8.
    发明申请
    Method for forming ceramic layer 有权
    陶瓷层形成方法

    公开(公告)号：US20060243368A1

    公开(公告)日：2006-11-02

    申请号：US11116291

    申请日：2005-04-28

    申请人： William Stowell ,  Terry Kent ,  Thomas Rentz ,  Jane Murphy ,  Daniel Ivkovich ,  Andrew Skoog

    发明人： William Stowell ,  Terry Kent ,  Thomas Rentz ,  Jane Murphy ,  Daniel Ivkovich ,  Andrew Skoog

    IPC分类号： C03B29/00 ,  B32B37/06

    CPC分类号： F01D5/288

    摘要： A method for forming a ceramic layer on the surface of a turbine component. This method comprises the following steps: (a) providing a turbine component having a surface; (b) providing at least one ceramic tape overlaying the component surface; and (c) manually pressing the at least one ceramic tape against the component surface at a temperature of from about 150° to about 700° F. (from about 66° to about 371° C.) so as to cause the at least one ceramic tape to adhere to the component surface.

    摘要翻译： 一种用于在涡轮机部件的表面上形成陶瓷层的方法。 该方法包括以下步骤：（a）提供具有表面的涡轮机部件; （b）提供覆盖所述部件表面的至少一个陶瓷带; 和（c）在约150°至约700°F（约66°至约371℃）的温度下手动地将至少一种陶瓷带压靠在部件表面上，以使至少一个 陶瓷胶带粘附在组件表面。