Patent ID: 8506253

Claim:
A rotor assembly for a gas turbine engine, comprising: a disc adapted for mounting to an engine shaft defining a longitudinal axis, the disc having two opposed faces; a flange extending axially from one of the two opposed faces of the disc along a circumference thereof, an edge of the flange having at least one positioning recess and a plurality of circumferentially spaced-apart fastener recesses, the at least one positioning recess being larger than the fastener recesses; a projection extending circumferentially along a radially facing surface of the flange; at least one balancing weight comprising a flange engaging portion and a hook portion, the flange engaging portion defining a flange receiving opening for mating with the flange of the disc, the hook portion extending from one end of the flange engaging portion and defining a projection receiving opening for mating with the projection, at least part of the flange engaging portion being sized to fit through the positioning recess when engaging the hook portion with the projection to lock the balancing weight in an axial direction with respect to the disc, the balancing weight having a fastener hole extending through at least part of the flange engaging portion, the fastener hole being aligned with one of the fastener recesses when the balancing weight is secured to the disc; and a fastener inserted through the fastener hole and the one of the fastener recesses to lock the balancing weight in a circumferential direction with respect to the disc.