Patent ID: 7186466

Claim:
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 ZrO 2 , HfO 2 and combinations thereof, said primary stabilizer being selected from the group consisting of Y 2 O 3 , Dy 2 O 3 , Er 2 O 3 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, wherein said group A dopant is selected such that the ionic radius of the group A dopant cation is smaller than the ionic radius of the primary stabilizer cation in said solid solution, and wherein said group B dopant is selected such that the ionic radius of the group B dopant cation is larger than the ionic radius of the primary stabilizer cation in said solid solution, the ratio of the molar percentages of group A dopant to group B dopant in said solid solution being between about 1:10 and about 10:1.