Coating process for gas turbine engine component with cooling holes

Patent metadata

Field	Value
Publication number	US-11143030-B2
Application number	US-201213725229-A
Country	US
Kind code	B2
Filing date	Dec 21, 2012
Priority date	Dec 21, 2012
Publication date	Oct 12, 2021
Grant date	Oct 12, 2021

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

First claim

What is claimed is:

1. 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.

2. The method as recited in claim 1 , further comprising removing all layers of a top coat of the prior coating.

3. The method as recited in claim 1 , further comprising removing all layers of a ceramic top coat of the prior coating.

4. The method as recited in claim 3 , further comprising removing at least one layer of a nickel alloy bond coat of the prior coating.

5. The method as recited in claim 1 , further comprising removing all layers of a ceramic top coat of the prior coating and at least one layer of the prior coating.

6. The method as recited in claim 1 , further comprising directing air through at least one of the multiple of cooling holes.

7. The method as recited in claim 1 , further comprising applying one coat layer without directing the gas through at least one of the multiple of cooling holes.

8. The method as recited in claim 1 , further comprising mapping the multiple of cooling holes.

9. The method as recited in claim 8 , further comprising finish drilling the multiple of cooling holes.

10. The method as recited in claim 1 , further comprising cleaning the multiple of cooling holes.

11. The method as recited in claim 1 , further comprising dressing the multiple of cooling holes to obtain a desired flow quality.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Burd Steven W
• Barron Alan C

Classifications

• C23C28/321

  with at least one metal alloy layer · CPC title

• F01D5/187

  Convection cooling · CPC title

• F05D2230/90

  Coating; Surface treatment · CPC title

• F01D5/288

  Protective coatings for blades · CPC title

• C23C28/34

  including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates · CPC title