CPC F01D 5/288 (2013.01) [B23K 26/364 (2015.10); C04B 35/48 (2013.01); C04B 35/505 (2013.01); F01D 5/18 (2013.01); F01D 5/186 (2013.01); F01D 9/02 (2013.01); F01D 25/08 (2013.01); F01D 25/12 (2013.01); F23M 5/02 (2013.01); F23R 3/002 (2013.01); F23R 3/007 (2013.01); C04B 2235/3244 (2013.01); C04B 2235/3246 (2013.01); F05D 2220/32 (2013.01); F05D 2230/13 (2013.01); F05D 2230/90 (2013.01); F05D 2240/11 (2013.01); F05D 2250/294 (2013.01); F05D 2260/202 (2013.01); F05D 2260/607 (2013.01); F05D 2300/6033 (2013.01); F23M 2900/05003 (2013.01); F23M 2900/05004 (2013.01); F23R 2900/00018 (2013.01); F23R 2900/03042 (2013.01)] | 20 Claims |
1. A coated component for a gas turbine engine, the coated component comprising:
a metal substrate defining an outer surface, the outer surface being a surface of the metal substrate that is facing an engine flowpath, the engine flowpath being a hot gas flow path; and
a ceramic coating disposed along the outer surface of the metal substrate and exposed to the engine flowpath, the ceramic coating having a thickness, wherein the ceramic coating comprises yttria stabilized zirconia,
wherein the ceramic coating comprises one or more cooling holes disposed in the ceramic coating and a plurality of slots disposed in the ceramic coating forming segments of ceramic coating material, each slot of the plurality of slots having a length, a width, and a depth,
wherein each slot of the plurality of slots is arranged such that a direction defined by its depth is perpendicular to a surface of the ceramic coating,
wherein the slots are disposed relative to the one or more cooling holes such that the slots do not pass through any of the one or more cooling holes, the slots extending through 80 percent or more of the thickness of the ceramic coating, and
wherein each segment of ceramic coating material overlies and defines a segment of the metal substrate, each segment of the metal substrate being substantially planar.
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