| 摘要 |
A thermal barrier coating which can be applied to a turbine engine component, and in which a yttria-stabilized zirconia layer and a molten silicate resistant layer are alternately deposited, a method for forming the thermal barrier coating, and a turbine engine component having the thermal barrier coating are provided. A thermal barrier coating system(18) comprises: a first yttria-stabilized zirconia layer(10); a first molten silicate resistant material layer(20) deposited onto the first yttria-stabilized zirconia layer; a second yttria-stabilized zirconia layer(22) deposited onto the first molten silicate resistant material layer; and a second molten silicate resistant material layer(24) deposited onto the second yttria-stabilized material layer. The thermal barrier coating system further comprises at least one additional yttria-stabilized zirconia layer and at least one additional molten silicate resistant material layer. The molten silicate resistant material comprises at least one oxide of a material selected from the group consisting of lanthanum, cerium, praseodymium, neodymium, promethium, samarium, europium, gadolinium, terbium, dysprosium, holmium, erbium, thulium, ytterbium, lutetium, scandium, indium, zirconium, hafnium, and titanium. The molten silicate resistant material comprises a gadolinia-stabilized zirconia. The gadolinia-stabilized zirconia consists of 25 to 99.9 wt.% of gadolinia and the balance of zirconia.
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