Patent ID: 9638037
Date: 2017-05-02
CPC Classifications: F01D,F04D,F05D,G01M

Claim:
1. A method of balancing a gas turbine engine rotor, the method comprising: providing a rotor having a disc and a circumferential array of blades extending radially outwardly from the disc, the disc having a balancing flange integrally connected thereto, the balancing flange being annular; measuring an unbalance of the rotor; determining a corresponding unbalance correction necessary to correct at least part of the unbalance; determining a configuration of a theoretical notch in the balancing flange that would create the unbalance correction, the configuration of the theoretical notch including a depth of the theoretical notch defined along the radial direction, an arc angle spanning a circumferential width of the theoretical notch, and a circumferential position of the theoretical notch; and creating the unbalance correction by removing material from the balancing flange to create a protuberance protruding radially relative to a remainder of the balancing flange, the protuberance having a height defined along the radial direction, the height corresponding to the depth of the theoretical notch, the protuberance having a circumferential width spanned by the arc angle of the theoretical notch, the protuberance having a circumferential position diametrically opposed to the circumferential position of the theoretical notch.