Using NiAl bonding coat, the canning part which is exposed to the mannered null

摘要

PROBLEM TO BE SOLVED: To provide a method for repairing a coated high pressure turbine blade, which has been exposed to engine operation, to restore coated airfoil contour dimensions of the blade.;SOLUTION: The method comprises removing a thermal barrier coating system, wherein a portion of the base metal substrate is removed, and determining the thickness of the base metal substrate removed. The portion of the base metal substrate removed has a thickness ▵t. The method also comprises applying a β phase NiAl overlay coating to the substrate, and determining the difference in thickness, ▵x, between the β phase NiAl overlay coating and the previously removed bond coat. The method further comprises reapplying the top ceramic thermal barrier coating to a nominal thickness of t+▵t-▵x, wherein ▵t compensates for the portion of removed base metal substrate. Advantageously, the coated airfoil contour dimensions of the high pressure turbine blade are restored to about the coated dimensions preceding the engine run.;COPYRIGHT: (C)2005,JPO&NCIPI