Patent ID: 9453413
Filing Date: 2016-09-27
CPC Classification: B23P,F01D,F04D,F05B,F05D,G01M,Y10T

Claim Text:
1. A rotor assembly for a gas turbine engine, the rotor assembly comprising a disk, a circumferential array of regularly spaced apart blades extending from the disk, a circumferential array of regularly spaced apart features provided on the disk and at least one balancing weight, each of the features being configured for receiving one of the at least one balancing weight, the circumferential array of features having an angular orientation relative to the circumferential array of blades such that all the features are each located at an at least substantially same offset angle from a stacking line of a respective adjacent one of the blades, the offset angle corresponding to an angular position on the disk where a stress concentration caused by one of the features is minimal.