Patent ID: 6789315
Filing Date: 2004-09-14
Classification: B23P,F01D,F05D,Y02T,Y10T

Abstract:
A method for extending a rounded trailing edge of a gas turbine nozzle vane, comprising the steps of:providing a gas turbine nozzle vane having a leading edge and the rounded trailing edge extending lengthwise between a root and a tip of the gas turbine nozzle vane, and a pair of opposed airfoil surfaces extending between the leading edge and the trailing edge to define an airfoil profile; affixing an extension wire to the trailing edge extending lengthwise along the trailing edge; applying a braze material to the extension wire and the trailing edge; and heating the braze material to a brazing temperature to melt at least a portion of the braze material and, upon cooling, to bond the extension wire and the braze material to the trailing edge, wherein there is no deposition of material other than a protective coating onto the airfoil surfaces.