초록 ▼

A multiphase ceramic thermal barrier coating is provided. The coating is adapted for use in high temperature applications in excess of about 1200° C., for coating superalloy components of a combustion turbine engine. The coating comprises a ceramic single or two oxide base layer disposed on the subs

A multiphase ceramic thermal barrier coating is provided. The coating is adapted for use in high temperature applications in excess of about 1200° C., for coating superalloy components of a combustion turbine engine. The coating comprises a ceramic single or two oxide base layer disposed on the substrate surface; and a ceramic oxide reaction product material disposed on the base layer, the reaction product comprising the reaction product of the base layer with a ceramic single or two oxide overlay layer.

대표청구항 ▼

1. A device adapted for use in a high temperature environment in excess of about 1200° C., comprising: a substrate having a surface; a ceramic single oxide base layer disposed on the substrate surface; and a ceramic oxide reaction product material disposed on the base layer, the reaction produc

1. A device adapted for use in a high temperature environment in excess of about 1200° C., comprising: a substrate having a surface; a ceramic single oxide base layer disposed on the substrate surface; and a ceramic oxide reaction product material disposed on the base layer, the reaction product comprising the reaction product of the base layer with a ceramic single oxide overlay layer, wherein the single oxide base layer comprises a composition having the formula CzOw and the single oxide overlay layer comprises a composition having the formula AxOy, wherein C and A are selected from the group consisting of: Al, Ca, Mg, Zr, Y, Sc, La, Ce, Pr, Nd, Pm, Sm, Eu, Gd, Dy, Ho, Er, Tm, Yb, Ta, Nb, z and x are selected from the group of integers consisting of: 1, 2, 3, and 4, and w and y are selected from the group of integers consisting of: 1, 2, 3, 4 and 5. 2. The device of claim 1, wherein the base layer is disposed on the substrate surface as columnar grain structure with discrete intercolumnar gaps or cracks that extend generally perpendicular to a top surface of the substrate. 3. The device of claim 2, wherein the base layer is disposed by a physical vapor deposition technique. 4. The device of claim 1, wherein the base layer is disposed on the substrate surface with a flat grain structure with discrete cracks or pores that extend generally parallel to the top surface of the substrate. 5. The device of claim 4, wherein the base layer is disposed by an air plasma spray technique. 6. The device of claim 1, wherein the substrate is a component of a combustion turbine engine. 7. The device of claim 6, wherein the component is selected from the group consisting of: blade, vane, transition, ring segment, bucket, nozzle, combustor can, and heat shield. 8. A device adapted for use in a high temperature environment in excess of about 1200° C., comprising: a substrate having a surface; a ceramic two-oxide base layer disposed on the substrate surface; and a ceramic oxide reaction product material disposed on the base layer, the reaction product comprising the reaction product of the base layer with a ceramic two-oxide overlay layer, wherein the two-oxide base layer comprises a composition having the formula (C,D)wOzand the two-oxide overlay layer comprises a composition having the formula (A,B)xOy, wherein C, D, A and B are selected from the group consisting of: Al, Ca, Mg, Zr, Y, Sc, La, Ce, Pr, Nd, Pm, Sm, Eu, Gd, Dy, Ho, Er, Tm, Yb, Ta, Nb, w and x are decimals ranging from about 0.5 to about 1.5, and z and y are decimals ranging from about 0.5 to about 2.0. 9. The device of claim 8, wherein the base layer is disposed on the substrate surface as columnar grain structure with discrete intercolumnar gaps or cracks that extend generally perpendicular to a top surface of the substrate. 10. The device of claim 9, wherein the base layer is disposed by a physical vapor deposition technique. 11. The device of claim 8, wherein the base layer is disposed on the substrate surface with a flat grain structure with discrete cracks or pores that extend generally parallel to the top surface of the substrate. 12. The device of claim 11, wherein the base layer is disposed by an air plasma spray technique. 13. The device of claim 8, wherein the substrate is a component of a combustion turbine engine. 14. The device of claim 13, wherein the component is selected from the group consisting of: blade, vane, transition, ring segment, bucket, nozzle, combustor can, and heat shield.