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AssigneesOhio Aerospace Institute, The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
InventorsDongming Zhu, Robert A. Miller
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A thermal barrier coating composition is provided. The composition has a base oxide, a primary stabilizer, and at least two additional cationic oxide dopants. Preferably, a pair of group A and group B defect cluster-promoting oxides is used in conjunction with the base and primary stabilizer oxides. The new thermal barrier coating is found to have significantly lower thermal conductivity and better sintering resistance. In preferred embodiments, the base oxide is selected from zirconia and hafnia. The group A and group B cluster-promoting oxide dopants preferably are selected such that the group A dopant has a smaller cationic radius than the primary stabilizer oxide, and so that the primary stabilizer oxide has a small cationic radius than that of the group B dopant.
A turbine blade structure comprising a metallic turbine blade substrate and a ceramic thermal barrier coating thereover, said ceramic thermal barrier coating comprising a ceramic alloy solid solution comprising 46–97 molar percent base oxide, 2–25 molar percent primary stabilizer, 0.5–25 molar percent group A dopant, and 0.5–25 molar percent group B dopant, said base oxide being selected from the group consisting of ZrO2, HfO2 and combinations thereof, said primary stabilizer being selected from the group consisting of Y2O3, Dy2O3, Er2O3 and combinations thereof, each of said group A dopant and said group B dopant being selected from the group consisting of rare earth oxides, alkaline earth metal oxides, transition metal oxides and combinations thereof, but excluding those species contained in said base oxide and primary stabilizer groups,
A combustor component for a jet engine, comprising a metallic combustor component substrate and a ceramic thermal barrier coating thereover, said ceramic thermal barrier coating comprising a ceramic alloy solid solution comprising 46–97 molar percent base oxide, 2–25 molar percent primary stabilizer, 0.5–25 molar percent group A dopant, and 0.5–25 molar percent group B dopant, said base oxide being selected from the group consisting of ZrO2, HfO2 and combinations thereof, said primary stabilizer being selected from the group consisting of Y2O3, Dy2O3, Er2O3 and combinations thereof, each of said group A dopant and said group B dopant being selected from the group consisting of rare earth oxides, alkaline earth metal oxides, transition metal oxides and combinations thereof, but excluding those species contained in said base oxide and primary stabilizer groups,
A structure comprising a metallic substrate and a ceramic thermal barrier coating over said substrate, said substrate being selected from the group consisting of a turbine blade and a combustor component for a jet engine, said ceramic thermal barrier coating comprising a ceramic alloy solid solution comprising 46–97 molar percent base oxide, 2–25 molar percent primary stabilizer, 0.5–25 molar percent group A dopant, and 0.5–25 molar percent group B dopant, said base oxide being selected from the group consisting of ZrO2, HfO2 and combinations thereof, said primary stabilizer being selected from the group consisting of Y2O3, Dy2O3, Er2O3 and combinations thereof, each of said group A dopant and said group B dopant being selected from the group consisting of rare earth oxides, alkaline earth metal oxides, transition metal oxides and combinations thereof, but excluding those species contained in said base oxide and primary stabilizer groups,
Dependencies are inferred from the claim text.