US2019284941A1PendingUtilityA1

Location-specific slurry based coatings for internally-cooled component and process therefor

Assignee: UNITED TECHNOLOGIES CORPPriority: Mar 16, 2018Filed: Mar 16, 2018Published: Sep 19, 2019
Est. expiryMar 16, 2038(~11.6 yrs left)· nominal 20-yr term from priority
C23C 16/045F05D 2230/90F01D 5/288F05D 2300/611F05D 2220/32C23C 2/04F01D 5/187C23C 16/06C23C 28/021C23C 10/24C23C 10/08F05D 2300/132
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Claims

Abstract

A method of coating a component including aluminizing an array of internal passageways within the component; and chromizing a portion of the array of internal passageways within the component. A component, including an airfoil having an array of aluminized internal passageways, the array of aluminized internal passageways chromized up to a demarcation.

Claims

exact text as granted — not AI-modified
What is claimed is: 
     
         1 . A method of coating a component, comprising:
 aluminizing an array of internal passageways within the component; and   chromizing a portion of the array of internal passageways within the component after aluminizing the array of internal passageways.   
     
     
         2 . The method as recited in  claim 1 , wherein chromizing the portion of the array of internal passageways comprises chromizing up to a demarcation. 
     
     
         3 . The method as recited in  claim 2 , wherein the demarcation is located at 20%-30% of an airfoil span of the component. 
     
     
         4 . The method as recited in  claim 2 , wherein the demarcation is at 25% of an airfoil span of the component. 
     
     
         5 . The method as recited in  claim 2 , wherein the demarcation is at an airfoil span location where local temperatures exceed approximately 1600 degree F. 
     
     
         6 . The method as recited in  claim 1 , wherein chromizing the portion of the array of internal passageways comprises applying a chromium slurry into the array of internal passageways within the component. 
     
     
         7 . The method as recited in  claim 6 , wherein the chromium slurry has a viscosity of 100-200 cp. 
     
     
         8 . The method as recited in  claim 1 , further comprising applying a thermal barrier coat atop a bond coat on an external surface of the component. 
     
     
         9 . A component, comprising:
 a substrate having an array of aluminized internal passageways within the component; and   a chromium-enriched coating within a portion of the array of internal passageways.   
     
     
         10 . The component as recited in  claim 9 , wherein the substrate comprises a superalloy. 
     
     
         11 . The component as recited in  claim 9 , wherein the chromium-enriched coating within the portion of the array of internal passageways is located at an inboard section of the component. 
     
     
         12 . The component as recited in  claim 9 , wherein the chromium-enriched coating within the portion of the array of internal passageways is located up to a demarcation that is located at 20%-30% of an airfoil span of the component. 
     
     
         13 . The component as recited in  claim 9 , wherein the chromium-enriched coating within the portion of the array of internal passageways is located up to a demarcation that is located at 25% of an airfoil span of the component. 
     
     
         14 . The component as recited in  claim 9 , wherein the chromium-enriched coating within the portion of the array of internal passageways is located up to an airfoil span location where local temperatures exceed approximately 1600 degree F. 
     
     
         15 . The component as recited in  claim 9 , wherein the chromium-enriched coating is 10-50 microns thick. 
     
     
         16 . A component, comprising:
 an airfoil having an array of aluminized internal passageways, the array of aluminized internal passageways chromized up to a demarcation.   
     
     
         17 . The component as recited in  claim 16 , wherein the demarcation is located at 20%-30% of a span of the airfoil. 
     
     
         18 . The component as recited in  claim 16 , wherein the demarcation is located at 25% of a span of the airfoil. 
     
     
         19 . The component as recited in  claim 16 , wherein the demarcation is located at an airfoil span where local temperatures exceed approximately 1600 degree F. 
     
     
         20 . The component as recited in  claim 16 , wherein the component is a turbine blade.

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