Composite thermal barrier coating with impermeable coating
AssigneeGeneral Electric Company
InventorsWayne Charles Hasz, Marcus Preston Borom, Curtis Alan Johnson
Life of this patent
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Abstract
A composite that protects thermal barrier coatings on parts from the deleterious effects of environmental contaminants at operating temperatures with an impermeable barrier coating is divulged. The thermal barrier coating composite decreases infiltration of molten contaminant compositions into openings in the thermal barrier coating to increase the life of the composite.
Claims5
A composite comprising a porous thermal barrier coating on a part with a continuous impermeable barrier coating adjacent to an outer surface of the thermal barrier coating where said impermeable barrier coating is dense and non-porous and where the impermeable barrier coating is about 0.2-250 micrometers thick and where said impermeable barrier coating is selected from the group consisting of tantalum oxide, scandium oxide, hafnium oxide, magnesium aluminum oxide, calcium zirconate, silicon carbide, tantalum carbide, titanium carbide, tungsten carbide, silicon oxycarbide, silicon nitride, zirconium nitride, tantalum nitride, boron nitride, chromium silicide, molybdenum silicide, tantalum silicide, titanium silicide, tungsten silicide, zirconium silicide, silver, gold, and alloys thereof.
A protected thermal barrier coated part comprising a part selected from the group consisting of nickel based alloys, cobalt based alloys, iron based alloys, and mixtures thereof, with a porous thermal barrier coating selected from the group consisting of a chemically stabilized zirconia selected from the group consisting of yttria-stabilized zirconia, scandia-stabilized zirconia, calcia-stabilized zirconia, and magnesia-stabilized zirconia, on said part and a dense and non-porous impermeable barrier coating selected from the group consisting of tantalum oxide, scandium oxide, hafnium oxide, magnesium aluminum oxide, calcium zirconate, silicon carbide, tantalum carbide, titanium carbide, tungsten carbide, silicon oxycarbide, silicon nitride, zirconium nitride, tantalum nitride, boron nitride, chromium silicide, molybdenum silicide, tantalum silicide, titanium silicide, tungsten silicide, zirconium silicide, silver, gold, and alloys thereof, in an amount of about 0.2-250 micrometers thick on an outer surface of said thermal barrier coating.
An article of manufacture for use in gas turbine engines comprising a part having a surface covered with a porous thermal barrier coating, where the porous thermal barrier coating is selected from the group consisting of yttria-stabilized zirconia, scandia-stabilized zirconia, calcia-stabilized zirconia, and magnesia-stabilized zirconia, and said thermal barrier coating having an outer surface covered with a dense and non-porous impermeable barrier coating in an amount of about 0.2-250 micrometers, where the dense and non-porous impermeable barrier coating is selected from the group consisting of tantalum oxide, scandium oxide, hafnium oxide, magnesium aluminum oxide, calcium zirconate, silicon carbide, tantalum carbide, titanium carbide, tungsten carbide, silicon oxycarbide, silicon nitride, zirconium nitride, tantalum nitride, boron nitride, chromium silicide, molybdenum silicide, tantalum silicide, titanium silicide, tungsten silicide, zirconium silicide, silver, gold, and alloys thereof.
Dependencies are inferred from the claim text.