Patent ID: 9327341
Filing Date: 2016-05-03
CPC Classification: B21D,Y10T

Claim Text:
1. A method of fabricating an integrally bladed rotor of a gas turbine engine, the integrally bladed rotor including a disc with an array of blades affixed to the disc, the blades extending radially outwardly and being circumferentially spaced apart, the method comprising: a) operating a milling machine to cut a blank of the integrally bladed rotor secured in a device for ensuring a machining position, thereby forming the integrally bladed rotor having the blades extending from the disc; b) scanning the fabricated integrally bladed rotor to generate a complete 3 dimensional profile of the integrally bladed rotor before removing the integrally bladed rotor from the device; c) calculating a center of gravity of the integrally bladed rotor based on the complete 3-dimensional profile of the integrally bladed rotor, and verifying whether or not the center of gravity is within an acceptable range with respect to a reference point of the integrally bladed rotor; and then d) removing the integrally bladed rotor from the device if the verification has a positive result.