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US 8,506,243 B2Granted
Segmented thermally insulating coating
AssigneeUnited Technologies Corporation
InventorsChristopher W. Strock, Gene Buchina, Susan M. Tholen
Life of this patent
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Abstract
A gas turbine article includes a substrate, a plurality of geometric surface features that protrude from the substrate, and a thermally insulating topcoat disposed over the plurality of geometric surface features. The thermally insulating topcoat includes segmented portions that are separated by faults that extend through the topcoat from the geometric surface features.
Claims25
A turbine article comprising:
- a substrate;
- a plurality of solid geometric surface features protruding from the substrate, each of the plurality of geometric features including a substantially uniform protrusion height extending from the substrate and a protrusion width, and a ratio of the protrusion width to the protrusion height is 1-10, with the protrusion height being at least 0.01 inches (0.254 millimeters);
- and
- a thermally insulating topcoat disposed over the plurality of geometric surface features, the thermally insulating topcoat including segmented portions that are separated by faults extending through the thermally insulating topcoat from the plurality of geometric surface features.
1 more element
A turbine comprising:
- a compressor section;
- a combustor fluidly connected with the compressor section;
- and
- a turbine section downstream from the combustor, the turbine section having a seal that includes a substrate extending between two circumferential sides, a leading edge, a trailing edge, an inner side for resisting hot engine exhaust gases from the combustor, and an outer side, with a plurality of solid geometric surface features protruding from the inner side and a thermally insulating topcoat disposed over the plurality of geometric surface features, each of the plurality of geometric features including a substantially uniform protrusion height extending from the substrate and a protrusion width, and a ratio of the protrusion width to the protrusion height is 1-10, with the protrusion height being at least 0.01 inches (0.254 millimeters), the thermally insulating topcoat including segmented portions that are separated by faults extending through the thermally insulating topcoat from the plurality of geometric surface features.
1 more element
A method of processing a gas turbine article, comprising:
- depositing a thermally insulating topcoat over a plurality of solid geometric surface features that protrude from a substrate such that the thermally insulating topcoat forms with faults that extend through the thermally insulating topcoat from the plurality of geometric surface features to separate segmented portions of the thermally insulating topcoat, each of the plurality of geometric features including a substantially uniform protrusion height extending from the substrate and a protrusion width, and a ratio of the protrusion width to the protrusion height is 1-10, with the protrusion height being at least 0.01 inches (0.254 millimeters).
Dependencies are inferred from the claim text.