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    Composition and method for a thermal coating system
    1.
    发明授权
    Composition and method for a thermal coating system 有权
    热涂层系统的组成和方法

    公开(公告)号：US08147922B2

    公开(公告)日：2012-04-03

    申请号：US12562527

    申请日：2009-09-18

    申请人： Andrew Jay Skoog ,  Jane Ann Murphy

    发明人： Andrew Jay Skoog ,  Jane Ann Murphy

    IPC分类号： B05D1/04

    CPC分类号： C23C24/00 ,  B05B5/043 ,  C23C4/12 ,  C23C4/18 ,  Y02T50/67 ,  Y10T428/26 ,  Y10T428/263 ,  Y10T428/264 ,  Y10T428/265

    摘要： A thermal coating includes a substrate, a first coating layer, and a second coating layer. The substrate is selected from the group consisting of superalloys and ceramic matrix composites. The first coating layer comprises an alumina powder, a silica binder, and at least one additive selected from either a first group or a second group. The second coating layer comprises at least one of zinc titanate or cerium oxide. A method for applying a thermal coating system includes spraying a bond coat mixture onto a substrate using a liquid electrostatic sprayer. The bond coat mixture comprises an alumina powder, a silica binder, and at least one additive selected from either a first group or a second group. The method further includes applying a top coat mixture onto the bond coat mixture, wherein the top coat mixture comprises at least one of zinc titanate or cerium oxide.

    摘要翻译： 热涂层包括基底，第一涂层和第二涂层。 基材选自超级合金和陶瓷基复合材料。 第一涂层包含氧化铝粉末，二氧化硅粘合剂和至少一种选自第一组或第二组的添加剂。 第二涂层包含钛酸锌或氧化铈中的至少一种。 施加热涂覆系统的方法包括使用液体静电喷涂器将粘合涂层混合物喷涂到基底上。 粘合涂层混合物包含氧化铝粉末，二氧化硅粘合剂和至少一种选自第一组或第二组的添加剂。 该方法还包括将面漆混合物施加到粘合涂层混合物上，其中顶涂层混合物包含钛酸锌或氧化铈中的至少一种。

    Field repairable high temperature smooth wear coating
    3.
    发明授权
    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：US07842335B2

    公开(公告)日：2010-11-30

    申请号：US11170471

    申请日：2005-06-29

    申请人： Andrew Jay Skoog ,  Jane Ann Murphy ,  William Randolph Stowell ,  David E. Caldwell

    发明人： Andrew Jay Skoog ,  Jane Ann Murphy ,  William Randolph Stowell ,  David E. Caldwell

    IPC分类号： B05D1/26 ,  B05D1/40 ,  B05D1/42 ,  B05D7/14

    CPC分类号： C23C24/08 ,  C09D1/00 ,  F01D5/288 ,  F05D2230/80 ,  F05D2230/90 ,  F23R2900/00019 ,  Y02T50/67 ,  Y02T50/671

    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, further including an accelerant, 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。 在清洁通过局部剥落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中的还含有促进剂的糊状混合物施加到部件的表面区域 ，并且使用机械装置任选地平滑。 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
    6.
    发明申请
    ELECTROSTATIC SPRAY FOR COATING AIRCRAFT ENGINE COMPONENTS 失效
    用于喷涂飞机发动机部件的静电喷雾

    公开(公告)号：US20090148614A1

    公开(公告)日：2009-06-11

    申请号：US12343852

    申请日：2008-12-24

    申请人： Matthew B. BUCZEK ,  Andrew J. SKOOG ,  Mark RECHTSTEINER ,  Jane Ann MURPHY

    发明人： Matthew B. BUCZEK ,  Andrew J. SKOOG ,  Mark RECHTSTEINER ,  Jane Ann MURPHY

    IPC分类号： B05D1/06

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

    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。

    Field repairable high temperature smooth wear coating
    9.
    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：US20070134408A1

    公开(公告)日：2007-06-14

    申请号：US11170471

    申请日：2005-06-29

    申请人： Andrew Jay Skoog ,  Jane Ann Murphy ,  William Randolph Stowell ,  David E. Caldwell

    发明人： Andrew Jay Skoog ,  Jane Ann Murphy ,  William Randolph Stowell ,  David E. Caldwell

    IPC分类号： B05D3/00 ,  B05D5/00 ,  B05D3/12 ,  B05D3/02

    CPC分类号： C23C24/08 ,  C09D1/00 ,  F01D5/288 ,  F05D2230/80 ,  F05D2230/90 ,  F23R2900/00019 ,  Y02T50/67 ,  Y02T50/671

    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, further including an accelerant, 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。 在清洁通过局部剥落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糊状混合物在粘合剂中，还包括促进剂，被施加到部件的表面区域 ，并且使用机械装置任选地平滑。 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。

    Sprayed-in thickness patterns
    10.
    发明授权
    Sprayed-in thickness patterns 有权

    公开(公告)号：US06663918B2

    公开(公告)日：2003-12-16

    申请号：US09853228

    申请日：2001-05-11

    申请人： Timothy Lance Manning ,  Timothy Ray Lattire ,  Michael Dwayne Rutter ,  Andrew Jay Skoog ,  Jane Ann Murphy

    发明人： Timothy Lance Manning ,  Timothy Ray Lattire ,  Michael Dwayne Rutter ,  Andrew Jay Skoog ,  Jane Ann Murphy

    IPC分类号： B05D102

    CPC分类号： B05B12/02 ,  B05B13/0431

    摘要： A differential thickness pattern can be induced in a coating that is sprayed on an aircraft engine part using a robotic system. The robotic system includes a spray mechanism with a triggering device to spray the coating on the aircraft engine part and a controller. The controller is used to move the spray mechanism along a predetermined path and to activate and deactivate the triggering device. To obtain the differential thickness pattern, a predetermined profile of the aircraft engine part corresponding to areas of the aircraft engine part requiring a thicker coating is integrated into a control program used by the controller. The controller uses the control program to activate and deactivate the triggering mechanism to limit the spraying of the coating to only those areas of the part in the predetermined profile to obtain a different coating thickness.