Patent ID: 7516547
Filing Date: 2009-04-14
Classification: C23C,F01D,F04D,F05D,Y02T,Y10T

Abstract:
1. A method for processing a gas turbine engine blade comprising the steps of: providing a gas turbine engine blade having an airfoil portion and a dovetail portion, the dovetail portion being opposed to the airfoil portion; peening the dovetail portion using first particles having a first preselected size; thereafter peening the dovetail portion using second particles having a second preselected size, wherein the second preselected size is smaller than the first preselected size; thereafter applying a copper-nickel-indium wear coating over a portion of an outer surface of the dovetail portion; and thereafter applying a lead-free dry film lubricant over the applied copper-nickel-indium wear coating including applying an aqueous lead-free lubricant coating layer over the applied copper-nickel-indium wear coating and curing the aqueous lead-free lubricant coating layer to remove water.