Cmas resistant thermal barrier coating

A thermal barrier coating and resistance technology, applied in the direction of coating, metal material coating process, plating of superimposed layers, etc., can solve the problems of metal peeling, accelerated oxidation, etc., and achieve the effect of reducing damage
CN101004142AInactive Publication Date: 2007-07-25UNITED TECH CORP
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
UNITED TECH CORP
Publication Date
2007-07-25
Estimated Expiration
Not applicable · inactive patent

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Abstract

A turbine engine component is provided which has a substrate and a thermal barrier coating (18) applied over the substrate (14). The thermal barrier coating comprises alternating layers (10, 20, 22, 24) of yttria-stabilized zirconia and a molten silicate resistant material. The molten silicate resistant outer layer (24) may be formed from 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 or may be formed from a gadolinia-stabilized zirconia. If desired, a metallic bond coat may be present between the substrate and the thermal barrier coating system. A method for forming the thermal barrier coating system of the present invention is described.
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Description

technical field

[0001] The present invention relates to a thermal barrier coating having alternating layers of yttria stabilized zirconia and fused silicate resistant layers applicable to turbine engine components, a method of forming the coating and a Turbine engine components having the coating. Background technique

[0002] Aging of turbine blades due to sand-related damage to thermal barrier coatings is a very important issue for all turbine engines used in desert environments. This type of damage requires removal of a running engine for overhaul.

[0003] Grit-related damage is caused by quicksand deposits penetrating the thermal barrier coating, which will cause any exposed metal to flake off and accelerate oxidation. Contents of the invention

[0004] According to the present invention, a coating system is provided that reduces grit-related damage on turbine engine components. The coating system broadly includes alternating layers of yttria stabilized zirconia an...

Claims

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