Patent ID: 9664111
Date: 2017-05-30
CPC Classifications: B23P,C23C,C25D,F01D,F02C,F05D,Y02T

Claim:
1. A method for filling cooling holes in a component of a gas turbine engine, the component having an outer surface and an inner surface and a plurality of first cooling holes, the plurality of first cooling holes extending between the outer surface and the inner surface of the component, the method comprising: removing a first thermal barrier coating from the outer surface of the component; filling the plurality of first cooling holes with a filling agent; removing excess filling agent from the outer surface of the component to level the outer surface of the component; curing the filling agent to block the plurality of first cooling holes; applying a second thermal barrier coating on the outer surface of the component and completely covering the cured filling agent; and installing a plurality of second cooling holes, the plurality of second cooling holes penetrating through the second thermal barrier coating and extending between the outer surface and the inner surface of the component.