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US 11,143,030 B2Granted
Coating process for gas turbine engine component with cooling holes
AssigneeRaytheon Technologies Corporation
InventorsSteven W. Burd, Alan C. Barron
Life of this patent
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Abstract
A method of coating a component having a multiple of cooling holes includes removing at least a portion of a prior coating; directing a gas through at least one of the multiple of cooling holes; and applying a coat layer while directing the gas through at least one of the
Claims11
A method of coating a component having a multiple of cooling holes comprising:
- removing at least a portion of a prior coating from the component;
- directing a gas through at least one of the multiple of cooling holes, wherein the at least one of the multiple of cooling holes extends in the component to an outlet;
- and
- applying a coat layer onto a surface of the component, wherein the coat layer is contiguous with the outlet on a side of the at least one of the multiple of cooling holes, wherein a centerline of the at least one of the multiple of cooling holes is angularly offset from the surface on the side by an acute angle, and wherein the gas is directed through the at least one of the multiple of cooling holes before and during the applying of the coat layer onto a portion of the surface of the component adjacent the outlet.
1 more element
Dependencies are inferred from the claim text.