Patent ID: 7536783
Filing Date: 2009-05-26
Classification: B23P,F01D,F05D,Y10T

Abstract:
1. A method for reconfiguring an airfoil of a turbine vane segment, comprising: engaging an outer shroud of the turbine vane segment by inserting reaction arms into recesses within an outer surface of the shroud, wherein the reaction arms are supported by a fixture; engaging an inner shroud of the turbine vane segment with a force exertion system for exerting a force in a direction that is generally tangential to the outer shroud; creating orifices in a convex side of an airfoil portion of the turbine vane segment proximate to the outer shroud while the turbine vane seament is engaged with the reaction arms and the force exertion system; heating the turbine vane segment to a temperature of between about 700 degrees F. and 750 degrees F.; and applying a force to the inner shroud with the force exertion system in a direction that is generally tangential to the outer shroud, said force being between about 2000 lbf and about 6000 lbf.