Patent ID: 6935817
Filing Date: 2005-08-30
Classification: B23C,Y10T

Abstract:
1. A method for machining an integrally bladed gas turbine engine rotor from a workpiece to form radially extending airfoil blades, comprising the steps of: a) mounting the workpiece on a workpiece holder of a numerically controlled multi-axis machining system, b) providing said multi-axis machining system with a circular machining tool defining a machining ring having concave and convex circumferential machining surfaces, and c) machining successive circumferentially spaced-apart airfoil blades at the periphery of the workpiece, under the direction of a machine program of the numerically controlled multi-axis machining system, by successively generating pairs of facing airfoil surfaces of consecutive airfoil blades at predetermined circumferential locations around the workpiece, wherein for each pair of facing airfoil surfaces, said concave and convex circumferential machining surfaces are located in a space between two consecutive airfoil blades to be defined to respectively machine a convex suction side and a concave pressure side of the two consecutive airfoil blades.