Patent ID: 9458763
Filing Date: 2016-10-04
CPC Classification: B32B,F01D,F02C,F23M,F23R,Y02T,Y10T

Claim Text:
1. A component for a turbomachine, comprising: a base; a high-temperature coating being arranged above the base, the base including a plurality of structural elements for connecting the base to the high-temperature coating, a cross-section of each of the structural elements having at least three different widths, including a base width at a lower end of the at least one structural element adjacent the base, a center width above the base width, and a tip width of a tip portion above the center width, where on average the center width is a greater width of each structural element, but is less than four times the base width; wherein the tip portion includes a shape facing outward from the base that is tapered to be more pointed than a hemi-sphere facing outward from the base and having the center width as a diameter, and wherein opposing flanks of the tip portion converge together at an angle less than 180°, on average; wherein the tapered outward facing tip portions of the plurality of structural elements form stress risers in the high-temperature coating for the creation of stress-relieving vertical cracks in the high-temperature coating.