Patent ID: 8631578
Filing Date: 2014-01-21
Classification: F01D,F16F,Y10T

Abstract:
1. 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 and a circumferential blade receiving edge therebetween adapted for mounting of a plurality of radially projecting blades, an axially extending flange integrally formed with the disc and projecting from one of the two opposed faces of the disc and annularly extending therearound at a radial location that is spaced apart from the circumferential blade receiving edge of the disc, an edge of the flange having at least one recess, the flange having a circumferential groove discontinuously extending about a circumference thereof; and at least one unitary balancing weight clip engaged solely to the axially extending flange and comprising a first flange engaging portion and a second flange engaging portion circumferentially spaced apart by a weight portion therebetween, the weight portion and the first and second flange engaging portions being integrally formed, the first and second flange engaging portions each being provided with a hook mating with the circumferential groove and the weight portion, the balancing weight clip being removably secured to the flange in a secured position wherein the hooks each engage the circumferential groove, the at least one balancing weight clip being immobile in an axial and circumferential direction when in the secured position, at least one of the first and second flange engaging portions being resiliently biased so that the first and second flange engaging portions are elastically moveable away from one another to receive the flange in a flange receiving opening defined by the first flange engaging portion, the second flange engaging portion and the weight portion.