| 摘要 |
A turbine airfoil with a thermal barrier coating applied to the surface for protection from a hot gas flow, where the TBC includes a plurality of micro-tubes extending from a cooling hole in the airfoil substrate and passing through the TBC to provide both reinforcement to and cooling of the TBC. The micro-tubes extend out from a separate hole and open onto the surface of the TBC, or a plurality of micro-tubes extends from a common hole and spread out from the hole. The micro-tubes are formed from nickel or another high temperature resistant material and have a diameter of about 0.009 inches.
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