Patent ID: 8353670

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 and a circumferential blade receiving edge therebetween adapted for mounting of a plurality of radially projecting blades; an axially extending flange projecting from one of the two opposed faces of the disc and annularly extending therearound at a radially location that is spaced apart from the circumferential blade receiving edge of the disc, the flange having a circumferential groove therein; and at least one balancing weight clip engaged solely to the axially extending flange and having a length which covers only a portion of the circumference of the annular axially extending flange, the balancing weight clip having a mass balancing the rotor assembly and comprising a first flange engaging portion, a second flange engaging portion and a weight portion therebetween, the weight portion and the first and second flange engaging portions defining a flange receiving opening, the first flange engaging portion being provided with a detent facing the second flange engaging portion and mating with the circumferential groove, the at least one balancing weight clip being removably secured to the flange in a secured position wherein the flange is received in the flange receiving opening and the detent engages the circumferential groove, the 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 elastically deformable so that the first and second flange engaging portions are elastically moveable away from one another to receive the flange in the flange receiving opening.