US2009208662A1PendingUtilityA1

Methods for Repairing a Workpiece

66
Assignee: UNITED TECHNOLOGIES CORPPriority: Nov 4, 2004Filed: Apr 30, 2009Published: Aug 20, 2009
Est. expiryNov 4, 2024(expired)· nominal 20-yr term from priority
C23C 4/11C23C 4/02C23C 4/134Y02T50/60C23C 4/073C23C 4/18
66
PatentIndex Score
0
Cited by
0
References
0
Claims

Abstract

A method for repairing a workpiece includes the steps of providing an unstripped, coated workpiece comprising a surface having a localized damage site; masking the workpiece about the localized damage site; generating a microplasma stream; and applying a first powdered material to the localized damage site using the microplasma stream; and applying a second powdered material to the workpiece surface using the microplasma stream. Another method for repairing a workpiece includes the steps of providing an unstripped, coated workpiece comprising a surface having a localized damage site; generating a microplasma stream; applying without a maskant a powdered metal alloy to the damage site using the microplasma stream; and dimensionally restoring the workpiece.

Claims

exact text as granted — not AI-modified
1 . A method for repairing a workpiece, comprising:
 providing an unstripped, coated workpiece comprising a surface having a localized damage site;   generating a microplasma stream;   applying without a maskant a powdered metal alloy to said localized damage site using said microplasma stream; and   dimensionally restoring said workpiece.   
   
   
       2 . The method of  claim 1 , wherein said powdered metal alloy is selected from the group consisting of nickel-aluminum, nickel-chromium, nickel chromium-aluminum, molybdenum and aluminum-silicon. 
   
   
       3 . The method of  claim 1 , wherein said powdered metal alloy is nickel-chrome-chromium carbide. 
   
   
       4 . The method of  claim 1 , wherein said workpiece is selected from the group consisting of fans, compressors, turbine casings, seals, plates, rings. 
   
   
       5 . The method of  claim 1 , wherein said workpiece is a gas turbine engine component. 
   
   
       6 . The method of  claim 1 , wherein said workpiece is a combustion chamber component. 
   
   
       7 . The method of  claim 1 , wherein said localized damage site comprises a spot or a chip.

Cited by (0)

No later patents cite this yet.

References (0)

No backward citations on record.