| 摘要 |
<p>The present invention relates to an airfoil arrangement (100) for a gas turbine. The airfoil arrangement (100) comprises an airfoil device (101, 110, 120) comprising a coated surface section (104, 106, 106') which represents at least a part of the total surface of the airfoil arrangement (100). The coated surface section (104, 106, 106') is coated with a bond coating (302) which comprises an oxide dispersion strengthened alloy. The bond coating (302) is coated with a thermal barrier coating (303).</p> |
