초록 ▼

A process of depositing a ceramic coating on an airfoil component and the component formed thereby is provided. The process includes depositing a bond coat on an airfoil component including on a trailing edge region thereof that defines a trailing edge of the airfoil component, within holes located

A process of depositing a ceramic coating on an airfoil component and the component formed thereby is provided. The process includes depositing a bond coat on an airfoil component including on a trailing edge region thereof that defines a trailing edge of the airfoil component, within holes located within the trailing edge region and spaced apart from the trailing edge, and on lands located within the trailing edge region and between the holes. A ceramic coating is then deposited on the bond coat including on the trailing edge region of the airfoil component, within the holes located within the trailing edge region, and on the lands between the holes. The ceramic coating within the holes is selectively removed without completely removing the ceramic coating on the trailing edge region and the lands between the holes.

대표청구항 ▼

1. A process comprising: depositing a bond coat on an airfoil component including on a trailing edge region thereof that defines a trailing edge of the airfoil component, within holes located within the trailing edge region and spaced apart from the trailing edge, and on lands located within the tra

1. A process comprising: depositing a bond coat on an airfoil component including on a trailing edge region thereof that defines a trailing edge of the airfoil component, within holes located within the trailing edge region and spaced apart from the trailing edge, and on lands located within the trailing edge region and between the holes;depositing a ceramic coating on the bond coat including on the trailing edge region of the airfoil component, within the holes located within the trailing edge region, and on the lands between the holes; and thenselectively removing the ceramic coating within the holes without completely removing the ceramic coating on the trailing edge region and the lands between the holes and without completely removing the bond coat from the holes. 2. The process according to claim 1, wherein the selectively removing step is performed with an ablative laser. 3. The process according to claim 1, wherein the ceramic coating is selectively removed from the trailing edge region to taper the ceramic coating so that the thickness of the ceramic coating upstream of each of the holes decreases in a downstream direction toward each of the holes. 4. The process according to claim 1, wherein the ceramic coating is selectively removed from the lands between the holes to taper the ceramic coating so that the thickness of the ceramic coating on the lands decreases in a downstream direction toward the trailing edge. 5. The process according to claim 1, wherein the holes are cooling holes of the component. 6. The process according to claim 2, wherein at least one of the holes has a shape that increases in cross-section in a downstream direction toward the trailing edge. 7. The process according to claim 1, wherein the component is a high pressure turbine blade. 8. The process according to claim 1, wherein the ceramic coating is selectively removed without completely removing the bond coat from the trailing edge region, and the lands between the holes. 9. The process according to claim 1, wherein the ceramic coating is selectively removed without damaging the bond coat in the holes, on the trailing edge region, and on the lands between the holes. 10. The airfoil component produced by the process of claim 1. 11. A process of forming the ceramic coating on an airfoil component, the airfoil component having a trailing edge region that defines a trailing edge of the airfoil component, holes located within the trailing edge region and spaced apart from the trailing edge, lands located within the trailing edge region and between the holes, a bond coat on surfaces of the airfoil component within the holes, and a ceramic coating on the trailing edge region of the airfoil component and on the lands between the holes but not within the holes, the process comprising: depositing a bond coat on the airfoil component including on a trailing edge region thereof that defines a trailing edge of the airfoil component, within holes located within the trailing edge region and spaced apart from the trailing edge, and on lands located within the trailing edge region and between the holes;depositing a ceramic coating on the bond coat including on the trailing edge region of the airfoil component, within the holes located within the trailing edge region, and on the lands between the holes; and thenselectively removing the ceramic coating within the holes with an ablative laser without completely removing the ceramic coating on the trailing edge region and the lands between the holes. 12. A process comprising: obtaining an airfoil component comprising a bond coat on the airfoil component, including on a trailing edge region the airfoil component that defines a trailing edge thereof, within the holes located within the trailing edge region and spaced apart from the trailing edge, and on lands located within the trailing edge region and between the holes, and a ceramic coating on the bond coat including on the trailing edge region of the airfoil component, within the holes located within the trailing edge region, and on the lands between the holes; and then selectively removing the ceramic coating within the holes without completely removing the ceramic coating on the trailing edge region and the lands between the holes and without completely removing the bond coat from the holes.