专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US06413578B1 Method for repairing a thermal barrier coating and repaired coating formed thereby 有权
标题翻译：用于修复由此形成的热障涂层和修补的涂层的方法
公开(公告)号：US06413578B1
公开(公告)日：2002-07-02
申请号：US09687721
申请日：2000-10-12
申请人： William R. Stowell , Robert A. Johnson , Andrew J. Skoog , Joseph Thomas Begovich , Thomas Walter Rentz , Jane Ann Murphy , Ching-Pang Lee , Dainel P. Ivkovich, Jr.
发明人： William R. Stowell , Robert A. Johnson , Andrew J. Skoog , Joseph Thomas Begovich , Thomas Walter Rentz , Jane Ann Murphy , Ching-Pang Lee , Dainel P. Ivkovich, Jr.
IPC分类号： B05D106
CPC分类号： C23C24/08 , Y02T50/67 , Y10T428/20 , Y10T428/24479 , Y10T428/24521 , Y10T428/25 , Y10T428/252
摘要： A method of 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 more particularly involves repairing a thermal barrier coating on a component that has suffered localized spallation of the thermal barrier coating. After cleaning the surface area of the component exposed by the localized spallation, a ceramic paste comprising a ceramic powder in a binder is applied to the surface area of the component. The binder is then reacted to yield a ceramic-containing repair coating that covers the surface area of the component and comprises the ceramic powder in a matrix of a material formed when the binder was reacted. The binder is preferably a ceramic precursor material that can be converted immediately to a ceramic or allowed to thermally decompose over time to form a ceramic, such that the repair coating has a ceramic matrix. The repair method can be performed while the component remains installed, e.g., in a gas turbine engine. Immediately after the reaction step, the gas turbine engine can resume operation during which the binder is further reacted/converted and the strength of the repair coating increases.
摘要翻译：在设计用于恶劣热环境中的部件（例如燃气涡轮发动机的涡轮机，燃烧器和增压器部件）上修复热障涂层的方法。该方法更具体地涉及在已经遭受热障涂层的局部剥落的部件上修复热障涂层。在清洁通过局部剥离暴露的部件的表面积之后，将包含粘合剂中的陶瓷粉末的陶瓷膏施加到部件的表面区域。然后使粘合剂反应以产生覆盖部件的表面积的含陶瓷的修补涂层，并且包含当粘合剂反应时形成的材料的基质中的陶瓷粉末。粘合剂优选是陶瓷前体材料，其可以立即转化成陶瓷或随时间而热分解形成陶瓷，使得修补涂层具有陶瓷基体。当部件保持安装时，例如在燃气涡轮发动机中，可以执行修理方法。在反应步骤之后，燃气涡轮发动机可以立即恢复操作，在此期间粘合剂进一步反应/转化，并且修复涂层的强度增加。

2. 发明授权

US06919121B2 Component with repaired thermal barrier coating 有权
标题翻译：具有修复热障涂层的组件
公开(公告)号：US06919121B2
公开(公告)日：2005-07-19
申请号：US10153929
申请日：2002-05-23
申请人： William R. Stowell , Robert A. Johnson , Andrew J. Skoog , Joseph Thomas Begovich , Thomas Walter Rentz , Jane Ann Murphy , Ching-Pang Lee , Dainel P. Ivkovich, Jr.
发明人： William R. Stowell , Robert A. Johnson , Andrew J. Skoog , Joseph Thomas Begovich , Thomas Walter Rentz , Jane Ann Murphy , Ching-Pang Lee , Dainel P. Ivkovich, Jr.
IPC分类号： F01D5/28 , C23C4/10 , C23C18/06 , C23C18/12 , C23C24/08 , C23C26/00 , C23C28/00 , F02C7/00 , B32B35/00
CPC分类号： C23C24/08 , Y02T50/67 , Y10T428/20 , Y10T428/24479 , Y10T428/24521 , Y10T428/25 , Y10T428/252
摘要： A method of repairing a thermal barrier coating (16) on a component (10) designed for use in a hostile thermal environment, such as turbine, combustor and augmentor components of a gas turbine engine. The method more particularly involves repairing a thermal barrier coating (16) on a component (10) that has suffered localized spallation (20) of the thermal barrier coating (16). After cleaning the surface area (22) of the component (10) exposed by the localized spallation (20), a ceramic paste (24) comprising a ceramic powder in a binder is applied to the surface area (22) of the component (10). The binder is then reacted to yield a ceramic-containing repair coating (26) that covers the surface area of the component and comprises the ceramic powder in a matrix of a material formed when the binder was reacted. The binder is preferably a ceramic precursor material that can be converted immediately to a ceramic or allowed to thermally decompose over time to form a ceramic, such that the repair coating (26) has a ceramic matrix. The repair method can be performed while the component (10) remains installed, e.g., in a gas turbine engine. Immediately after the reaction step, the gas turbine engine can resume operation during which the binder is further reacted/converted and the strength of the repair coating increases.
摘要翻译：修复设计用于恶劣热环境的部件（10）上的热障涂层（16）的方法，所述部件（10）用于燃气涡轮发动机的涡轮机，燃烧器和增压器部件。该方法更具体地涉及修复已经遭受热隔离涂层（16）的局部剥落（20）的部件（10）上的热障涂层（16）。在清洁通过局部剥离（20）暴露的组分（10）的表面积（22）之后，将包含粘合剂中的陶瓷粉末的陶瓷浆料（24）施加到组分（10）的表面区域（22））。然后使粘合剂反应以产生覆盖部件的表面积的含陶瓷的修补涂层（26），并且将包含在粘合剂反应时形成的材料的基质中的陶瓷粉末。粘合剂优选是陶瓷前体材料，其可以立即转化为陶瓷或随时间而热分解形成陶瓷，使得修补涂层（26）具有陶瓷基体。可以在组件（10）保持安装（例如，在燃气涡轮发动机中）的情况下执行修理方法。在反应步骤之后，燃气涡轮发动机可以立即恢复操作，在此期间粘合剂进一步反应/转化，并且修复涂层的强度增加。

3. 发明授权

US06465090B1 Protective coating for thermal barrier coatings and coating method therefor 有权
标题翻译：防护涂层及其涂覆方法的保护涂层
公开(公告)号：US06465090B1
公开(公告)日：2002-10-15
申请号：US09690860
申请日：2000-10-17
申请人： William R. Stowell , Joseph Thomas Begovich , Thomas Walter Rentz , Glen A. MacMillan , John Greene , Jane Ann Murphy , Dainel P. Ivkovich, Jr. , Andrew J. Skoog
发明人： William R. Stowell , Joseph Thomas Begovich , Thomas Walter Rentz , Glen A. MacMillan , John Greene , Jane Ann Murphy , Dainel P. Ivkovich, Jr. , Andrew J. Skoog
IPC分类号： F03B312
CPC分类号： C04B41/52 , C04B41/009 , C23C24/08 , C23C28/00 , F01D5/288 , F23M5/00 , F23M2900/05004 , F23R3/007 , Y10T428/25 , Y10T428/252 , Y10T428/26 , C04B41/4535 , C04B41/4554 , C04B41/5031 , C04B41/5035 , C04B41/5037 , C04B41/5041 , C04B41/5027 , C04B35/00 , C04B35/48
摘要： A protective coating and coating method for protecting a thermal barrier coating (TBC) on a component, such as a component of a gas turbine engine. The protective coating comprises alumina particles in a silica-containing matrix, and may be substantially homogeneous or formed of multiple layers having different compositions. The composition and relative amounts of alumina and matrix material in the protective coating enable the coating to react with molten compounds containing calcia, magnesia, alumina and/or silica (CMAS), forming a compound with a melting temperature that is significantly higher than CMAS. As such, infiltration of molten CMAS into the TBC is significantly reduced or entirely avoided.
摘要翻译：用于保护诸如燃气涡轮发动机的部件的部件上的热障涂层（TBC）的保护涂层和涂覆方法。保护涂层包含含二氧化硅的基质中的氧化铝颗粒，并且可以是基本均匀的或由具有不同组成的多层形成。保护涂层中的氧化铝和基体材料的组成和相对量使得涂层能够与含有氧化钙，氧化镁和/或二氧化硅（CMAS）的熔融化合物反应，形成的熔融温度明显高于CMAS。因此，熔融CMAS浸入TBC中显着降低或完全避免。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式