Thermal barrier coating system
AssigneeThe United States of America as represented by the Administrator of the National Aeronautics and Space Administration
InventorStephan Stecura
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AssigneeThe United States of America as represented by the Administrator of the National Aeronautics and Space Administration
InventorStephan Stecura
Estimating the term…
This invention relates to a high temperature oxidation resistant thermal barrier coating system for a nickel-, cobalt-, or iron-base alloy substrate. An inner metal bond coating contacts the substrate, and a thermal barrier coating covers the bond coating. NiCrAlR, FeCrAlR, and CoCrAlR alloys have been satisfactory as bond coating compositions where R=Y or Yb. These alloys contain, by weight, 24.9-36.7% chromium, 5.4-18.5% aluminum, and 0.05 to 1.55% yttrium or 0.05 to 0.53% ytterbium. The coatings containing ytterbium are preferred over those containing yttrium. An outer thermal barrier coating of partially stabilized zirconium oxide (zirconia) which is between 6% and 8%, by weight, of yttrium oxide (yttria) covers the bond coating. Partial stabilization provides a material with superior durability. Partially stabilized zirconia consists of mixtures of cubic, tetragonal, and monoclinic phases.
A coated article of manufacture having a duplex thermal barrier coating system comprising
A coated article of manufacture having a duplex thermal barrier coating system comprising
Dependencies are inferred from the claim text.