Patent ID: 8100655
Filing Date: 2012-01-24
Classification: B23C,F01D,Y10T

Abstract:
1. A method of machining an airfoil root fillet at a transition from an airfoil surface to a gaspath surface of a gas turbine engine, the method comprising: providing a single flank milling cutter having a primary conical milling surface and a secondary tip milling surface, said secondary tip milling surface defining a compound curve; and using said single flank milling cutter to machine both the airfoil surface and the airfoil root fillet, including using said secondary tip milling surface of said flank milling cutter to generate a compound curve at the transition between the airfoil surface and the gaspath surface, said compound curve having a curvature which generally increases towards said gaspath surface, wherein said compound curve defined by the airfoil root fillet has a primary curve segment extending from the airfoil surface and a secondary curve segment merging into said gaspath surface, wherein said secondary curve segment has a curvature which is about 5 times greater than the curvature of said primary curve segment.