Patent ID: 7806662

Claim:
A blade retention system for use with a rotor disc of a gas turbine engine, the rotor disc having a plurality of spaced-apart and circumferentially-disposed blade retention slots extending from a first side face to a second side face of the rotor disc, the device comprising: an annular sealing plate having two opposite first and second side faces and a plurality of spaced-apart holes in the annular sealing plate, extending from one said side face to another said side face; and a plurality of spaced-apart blade retention tabs having opposite first and second ends and a radially-orientated corrugated profile, the first ends of the tabs being bent against the second side face of the annular sealing plate, each tab being inserted through one of said spaced-apart holes and through a bottom portion of a respective one of the blade retention slots when the first side face of the sealing plate is positioned against one of the side faces of the rotor disc and covers an end side of the blade retention slots, the second end of each tab extending beyond the other of the side faces of the rotor disc and being bent against the other of the side faces to axially retain blades with reference to the rotor disc.