Coating system for internally-cooled component and process therefor

Patent metadata

Field	Value
Publication number	US-11427904-B2
Application number	US-201514887447-A
Country	US
Kind code	B2
Filing date	Oct 20, 2015
Priority date	Oct 20, 2014
Publication date	Aug 30, 2022
Grant date	Aug 30, 2022

Abstract

A method of coating includes applying a metallic coating slurry without a filler to a component; draining the metallic coating slurry; drying the metallic coating slurry to drive off the organic binder; and heat treating the component.

First claim

What is claimed:

1. A method of coating an interior of an internally cooled turbine component for a gas turbine engine, comprising:
flowing a chromium slurry without a filler into an array of internal passageways within an airfoil section of an internally cooled turbine component, the chromium slurry defines a viscosity of about 100-200 cp, wherein the chromium slurry, in terms of weight percentages, comprises 48.5-68% by weight Chromium powder, about 0.9-3.4% by weight Chromium Chloride (CrCl3) particles, and about 30-50% by weight organic binder;
draining the chromium slurry from within the array of internal passageways;
drying the chromium slurry to drive off the organic binder; and
heat treating the component.

2. The method as recited in claim 1 , wherein the component is a blade.

3. The method as recited in claim 1 , wherein the component is a vane.

4. The method as recited in claim 1 , wherein the drying comprises drying at about 200F for about 1 hour.

5. The method as recited in claim 1 , wherein the heat treating comprises heat treating at about 1925F (1052C) to about 2000F (1093C), for a time of from about 5 to about 6 hours.

6. The method as recited in claim 1 , further comprising:
cathodic arc depositing a bondcoat to an external surface of the component.

7. The method as recited in claim 6 , further comprising applying a thermal barrier coating atop the bondcoat.

8. A method of coating an interior of an internally cooled turbine component for a gas turbine engine, comprising:
flowing a chromium slurry without a filler that defines a viscosity of about 100-200 cp into an array of internal passageways within an airfoil section of a component, wherein the chromium slurry, in terms of weight percentages, comprises 48.5-68% by weight Chromium powder, about 0.9-3.4% by weight Chromium Chloride (CrCl3) particles, and about 30-50% by weight organic binder;
draining the chromium slurry from within the array of internal passageways within the component;
drying the chromium slurry to drive off the organic binder at about 200F for about 1 hour;
heat treating the component at about 1925F (1052C) to about 2000F (1093C) for about 5 to about 6 hours;
cathodic arc depositing a bondcoat to an external surface of the component; and
applying a thermal barrier coating atop the bondcoat.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Task Michael N
• Hazel Brian T
• Collins Kevin L
• Minor Michael J

Classifications

• C21D9/0068 Primary

  for particular articles not mentioned below · CPC title

• C23C24/08

  by application of heat or pressure and heat (C23C24/04 takes precedence) · CPC title

• C23C10/32 Primary

  Chromising · CPC title

• C23C28/347

  with layers adapted for cutting tools or wear applications · CPC title

• F01D5/288

  Protective coatings for blades · CPC title