Rotor assembly with rotor disc lip

A rotor assembly for a gas turbine engine, comprising:

• a plurality of blades having a blade root portion with a profiled shape, an airfoil portion and platform segments extending laterally from sides of the airfoil section into opposing relationship with corresponding platform segments of adjacent ones of the blades;
• and
• a rotor disc having a front end portion and an opposite rear end portion axially spaced apart from one another, and a peripheral surface circumferentially extending about the disc between the front end portion and the rear end portion, a plurality of fixing members defined therein through the peripheral surface and circumferentially spaced apart from one another, the fixing members extending axially from the front end portion to the rear end portion of the disc, profiled slots defined between pairs of adjacent ones of the fixing members and axially receiving a respective one of the blade root portions, a plurality of disc lips projecting axially forward from a surrounding surface of the disc in the front end portion and an outer periphery of the plurality of disc lips extending radially outward from a surrounding portion of the peripheral surface of the disc, the plurality of disc lips disposed at respective tip portions of the Plurality of fixing members, adjacent a leading edge of the peripheral surface of the disc where the platform segments of adjacent ones of the blades and the plurality of disc lips interface.