초록 ▼

A thermal barrier coating (18) having a less dense bottom layer (20) and a more dense top layer (22) with a plurality of segmentation gaps (28) formed in the top layer to provide thermal strain relief. The top layer may be at least 95% of the theoretical density in order to minimize the densificatio

A thermal barrier coating (18) having a less dense bottom layer (20) and a more dense top layer (22) with a plurality of segmentation gaps (28) formed in the top layer to provide thermal strain relief. The top layer may be at least 95% of the theoretical density in order to minimize the densification effect during long term operation, and the bottom layer may be no more than 95% of the theoretical density in order to optimize the thermal insulation and strain tolerance properties of the coating. The gaps are formed by a laser engraving process controlled to limit the size of the surface opening to no more than 50 microns in order to limit the aerodynamic impact of the gaps for combustion turbine applications. The laser engraving process is also controlled to form a generally U-shaped bottom geometry (54) in the gaps in order to minimize the stress concentration effect.

대표청구항 ▼

1. A device adapted for use in a high temperature environment, the device comprising: a substrate having a surface; a layer of ceramic insulating material disposed on the substrate surface, the layer of ceramic insulating material having a first as-deposited void fraction in a bottom portion pro

1. A device adapted for use in a high temperature environment, the device comprising: a substrate having a surface; a layer of ceramic insulating material disposed on the substrate surface, the layer of ceramic insulating material having a first as-deposited void fraction in a bottom portion proximate the substrate surface and a second as-deposited void fraction, less than the first as-deposited void fraction, in a top portion proximate a top surface of the layer of ceramic insulating material; and a plurality of segments having respective predetermined sizes and shapes defined by continuous gaps formed in the top surface of the layer of ceramic insulating material. 2. The device of claim 1, further comprising the gaps having a width at the surface of the layer of ceramic insulating material of no more than 50 microns. 3. The device of claim 1, further comprising the gaps having a width at the surface of the layer of ceramic insulating material of no more than 25 microns. 4. The device of claim 1, further comprising the gaps having a generally U-shaped bottom geometry. 5. The device of claim 1, further comprising the layer of ceramic insulating material having a second as-deposited void fraction of no more than 5%. 6. The device of claim 5, further comprising the layer of ceramic insulating material having a first as-deposited void fraction in the range of 5-20%. 7. The device of claim 1, wherein the gaps extend through a complete thickness of the top portion of the layer of ceramic insulating material but not to the substrate surface. 8. A device for use as an airfoil in a high temperature environment, the device comprising: a substrate having a surface; a layer of a ceramic insulating material disposed on the substrate surface; and a plurality of laser-engraved continuous gaps defining a plurality of segments having predetermined sizes and shapes in a top surface of the layer of ceramic insulating material, the gaps having a width at the top surface of no more than 50 microns and extending through only a portion of a thickness of the layer of ceramic insulating material but not to the substrate surface. 9. The device of claim 8, further comprising the gaps having a generally U-shaped bottom geometry. 10. The device of claim 8, further comprising the layer of ceramic insulating material having a first as-deposited void fraction in a bottom layer proximate the substrate surface and a second as-deposited void fraction, less than the first as-deposited void fraction, in a top layer proximate the top surface of the layer of ceramic insulating material. 11. The device of claim 8, wherein the substrate is a combustion turbine blade or vane. 12. The device of claim 8, wherein the ceramic insulating material comprises zirconium oxide or a pyrochlore.