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Thermal barrier coating system comprising rare earth aluminate layer for improved CMAS penetration resistance and coated article
Thermal barrier coating system comprising rare earth aluminate layer for improved CMAS penetration resistance and coated article
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机译:包括稀土铝酸盐层以提高CMAS耐穿透性的热障涂层系统和涂层制品
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摘要
Thermal barrier coating systems for use with hot section components of a gas turbine engine include an inner layer overlying a bond coated substrate and a top layer overlying at least a portion of the inner layer. The inner layer includes a thermal barrier material such as yttria-stabilized zirconia. The top layer includes a rare earth aluminate. The thicknesses and microstructures of the layers may be varied depending on the type of component to be coated. Articles incorporating the thermal barrier coating system exhibit improved resistance to CMAS infiltration.
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