Patent ID: 9511457
Filing Date: 2016-12-06
CPC Classification: B23P,F01D,F05D,F16F,Y10T

Claim Text:
1. A method of balancing a gas turbine engine rotor, the method comprising: a) obtaining a rotor disc with a circumferential array of tabs projecting from a peripheral rim of the disc and with stress shielding scallops between the tabs, wherein the tabs are created by machining the stress shielding scallops in a radially inner surface of the peripheral rim of the disc, the tabs projecting radially inwardly from the peripheral rim, the tabs having a predetermined initial weight; b) measuring a rotational imbalance of the rotor; and then c) correcting at least a part of the measured imbalance by removing material from at least one of the tabs to reduce the predetermined initial weight thereof to a reduced weight.