Corrosion inhibiting ceramic coating and method of application
    1.
    发明申请
    Corrosion inhibiting ceramic coating and method of application 审中-公开
    防腐陶瓷涂层及其应用方法

    公开(公告)号:US20070128447A1

    公开(公告)日:2007-06-07

    申请号:US11293448

    申请日:2005-12-02

    IPC分类号: B05D3/02 B05D1/02

    摘要: A corrosion resistant coating for engine components such as turbine disks, turbine seal elements and turbine shafts. This coating may also find application to other turbine components that are subjected to high temperatures and corrosive environments, such as turbine components located within or on the boundary of the gas fluid flow path, including for example turbine blades, turbine vanes, liners and exhaust flaps. The corrosion resistant coating of the present invention in service on a gas turbine component includes a glassy ceramic matrix wherein the glassy matrix is silica-based and particles selected from the group consisting of refractory oxide particles, MCrAlX particles and combinations of these particles, substantially uniformly distributed within the matrix. The refractory oxide and/or the MCrAlX provides the coating with corrosion resistance. Importantly the coating of the present invention has a coefficient of thermal expansion (CTE) greater than alumina. The CTE of the coating is sufficiently close to the substrate material, that is, the component to which it is applied, such that the coating does not spall after frequent engine cycling at elevated temperature

    摘要翻译: 发动机部件如涡轮盘,涡轮密封元件和涡轮轴的耐腐蚀涂层。 该涂层还可以应用于经受高温和腐蚀性环境的其它涡轮机部件,例如位于气体流体流路的边界内或其上的涡轮机部件,包括例如涡轮机叶片,涡轮叶片,衬管和排气翼 。 在燃气轮机部件上使用的本发明的耐腐蚀涂层包括玻璃质陶瓷基体,其中玻璃质基质是基于二氧化硅的,并且选自由耐火氧化物颗粒,MCrAlX颗粒和这些颗粒的组合组成的组的颗粒,基本均匀 分布在矩阵内。 难熔氧化物和/或MCrAlX为涂层提供耐腐蚀性。 重要的是,本发明的涂层具有比氧化铝大的热膨胀系数(CTE)。 涂层的CTE足够接近基材,即其所施加的组分,使得涂层在高温下经常发动机循环后不会分散

    COMPOSITE THERMAL BARRIER COATING WITH IMPROVED IMPACT AND EROSION RESISTANCE
    6.
    发明申请
    COMPOSITE THERMAL BARRIER COATING WITH IMPROVED IMPACT AND EROSION RESISTANCE 有权
    具有改进的冲击和耐腐蚀性的复合热障涂层

    公开(公告)号:US20070141367A1

    公开(公告)日:2007-06-21

    申请号:US11306125

    申请日:2005-12-16

    IPC分类号: B32B15/04

    摘要: A thermal barrier coating (TBC) for a component intended for use in a hostile environment, such as a component of a gas turbine engine. The TBC exhibits improved impact and erosion resistance as a result of being a composite material consisting essentially of particles of a ceramic reinforcement material dispersed in a ceramic matrix material. The ceramic reinforcement material has a yield strength greater than the ceramic matrix material at about 1100° C., and the particles of the ceramic reinforcement material have an average maximum dimension of greater than five micrometers.

    摘要翻译: 用于在敌对环境中使用的组件的热障涂层(TBC),例如燃气涡轮发动机的部件。 作为基本上由分散在陶瓷基体材料中的陶瓷增强材料的颗粒组成的复合材料,TBC显示出改善的耐冲击性和耐腐蚀性。 陶瓷增强材料在约1100℃下的屈服强度大于陶瓷基体材料,并且陶瓷增强材料的颗粒的平均最大尺寸大于5微米。