Patent ID: 7185433

Claim:
A method of repairing a turbine nozzle segment, comprising: providing an engine-run turbine nozzle segment having at least one vane disposed between outer and inner bands, wherein said outer band and said at least one vane are previously replaced components of said segment and said inner band is an original component of said segment; separating said inner band from said nozzle segment; repairing damage in at least one of said outer band and said at least one vane; and joining said outer band and said at least one vane to a newly manufactured replacement inner band segment, said replacement inner band segment including: a replacement inner band having opposed first and second sides; said first side having at least one airfoil-shaped recess formed therein for receiving said vane; and said second side having a raised collar integrally formed therein; wherein the step of joining said outer band and said vane to said replacement inner band segment comprises: providing a slot in said collar; inserting a portion of said vane into said slot; and joining said vane to said collar and to said replacement inner band segment.