US2013323066A1PendingUtilityA1

Maskant for fluoride ion cleaning

42
Individually held — no corporate assignee on recordPriority: May 31, 2012Filed: May 31, 2012Published: Dec 5, 2013
Est. expiryMay 31, 2032(~5.9 yrs left)· nominal 20-yr term from priority
Inventors:Monika D. Kinstler
B23P 6/045C23G 5/00C23C 18/1689F01D 5/005C23C 18/32C23C 18/1616
42
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Claims

Abstract

A method of treating a surface includes the steps of providing a plating including at least some nickel over a nickel alloy surface in a thickness less than 0.0005″ (0.001 cm), and exposing the surface to a fluoride ion cleaning to remove impurities on the surface, and leaving at least some of the plating.

Claims

exact text as granted — not AI-modified
1 . A method of treating a surface comprising the steps of:
 a) providing a plating including at least some nickel over a nickel alloy surface in a thickness less than 0.0005″ (0.001 cm); and   b) exposing said surface to a fluoride ion cleaning to remove impurities on the surface, and leaving at least some of said plating.   
     
     
         2 . The method as set forth in  claim 1 , wherein said nickel alloy includes at least one of aluminum and titanium. 
     
     
         3 . The method as set forth in  claim 2 , wherein said fluoride ion cleaning may be hydrogen fluoride ion cleaning. 
     
     
         4 . The method as set forth in  claim 3 , wherein said surface is part of a component having a crack with oxides to be cleaned by said fluoride ion cleaning. 
     
     
         5 . The method as set forth in  claim 4 , wherein said component has an airfoil. 
     
     
         6 . The method as set forth in  claim 5 , wherein said component is a gas turbine engine component. 
     
     
         7 . The method as set forth in  claim 4 , wherein said nickel plating is deposited in a thickness that is generally less than a depth of said crack. 
     
     
         8 . The method as set forth in  claim 4 , wherein said crack is repaired after said fluoride ion cleaning. 
     
     
         9 . The method as set forth in  claim 4 , wherein said component has internal cavities, and an inner wall spaced inwardly from an outer wall, and said crack is in said inner wall, and the plating of step (a) on said inner wall is done with electroless plating technique. 
     
     
         10 . The method as set forth in  claim 9 , wherein said plating is provided by a nickel alloy. 
     
     
         11 . The method as set forth in  claim 9 , wherein said crack extending from said inner wall to said outer wall, and the plating of step (a) is done on both said outer wall and said inner wall. 
     
     
         12 . The method as set forth in  claim 4 , wherein a thickness of said nickel plating is greater than or equal to about 0.0001″ (0.000254 cm) and less than or equal to about 0.0002″ (0.0005 cm). 
     
     
         13 . The method as set forth in  claim 1 , wherein said plating is deposited in a thickness that is generally less than the depth of said crack. 
     
     
         14 . The method as set forth in  claim 13 , wherein a thickness of said plating is greater than or equal to about 0.0001″ (0.000254 cm) and less than or equal to about 0.0002″ (0.0005 cm). 
     
     
         15 . A method of repair comprising the steps of:
 a) providing a plating including at least some nickel over a nickel alloy component that has a crack to be repaired the plating being less than 0.0005″ (0.001 cm) thick;   b) exposing said component to a fluoride ion cleaning to remove impurities in the crack, and leaving at least some of said plating; and   c) repairing the crack in the component.   
     
     
         16 . The method as set forth in  claim 15 , wherein said component has internal cavities, and an inner wall spaced inwardly from an outer wall, and said crack is in said inner wall, and the plating of step (a) is done on said inner wall with electroless plating technique. 
     
     
         17 . The method as set forth in  claim 16 , wherein said plating is provided by a nickel alloy. 
     
     
         18 . The method as set forth in  claim 15 , wherein said nickel plating is deposited in a thickness that is generally less than the depth of said crack. 
     
     
         19 . The method as set forth in  claim 15 , wherein a thickness of said nickel plating is greater than or equal to about 0.0001″ (0.000254 cm) and less than or equal to about 0.0002″ (0.0005 cm). 
     
     
         20 . A gas turbine engine component comprising:
 an airfoil formed of a nickel alloy include at least one or aluminum and titanium; and   nickel plating over a surface of said airfoil, said nickel plating being deposited in a thickness of greater than or equal to about 0.0001″ (0.000254 cm) and less than or equal to about 0.0002″ (0.0005 cm); and   a repaired crack.

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