Patent ID: 8091230
Filing Date: 2012-01-10
Classification: B23H,F01D,F04D,F05D,Y02T,Y10T

Abstract:
1. A method of forming a closely spaced radial array of overlapping airfoils for use in an axial compressor or turbine in a gas turbine engine from a solid planar blank of material having a perimeter edge, each airfoil comprising a concave pressure side and opposed convex suction side extending axially between opposing side edges and twisted lengthwise, comprising: providing a cutting tool in the form of an elongate and substantially rigid element other than a wire, providing a tool holder comprising at least one post entirely outside the plane of said planar blank for fixedly engaging said cutting tool in an orientation in which at least a portion of said cutting tool intersects said plane of said blank, said tool holder disposed to advance in a direction parallel to said plane of said workpiece so as to advance said cutting tool towards and past said perimeter edge, removing material from said a solid blank to leave the blades or vanes upstanding as the residual material of the blank, removal being effected by a change of state of the material induced by proximity to said advancing tool, and the tool turning as it advances, whereby to generate a surface of said shaped blade or vane.