Rotor assembly with blade sealing tab

A method of sealing a circumferential joint between blades removably connectable to a rotor disc for a gas turbine engine, the circumferential joint located at an interface between the blades and the rotor disc at a downstream face thereof, the rotor disc having a front face, a rear face and a peripheral surface, a plurality of slots circumferentially spaced about and formed in the peripheral surface, and a plurality of fixing members extending from the front face to the rear face and circumferentially disposed between adjacent slots, the peripheral surface of the disc forming a radially outer tip of the fixing members, the method comprising:

• matingly engaging a first blade root of a first one of the blades in a first one of the slots, abutting a portion of a rear surface of the first blade root against a sealing tab projecting radially outward relative to the radially outer tip of one of the fixing members, the sealing tab axially disposed at a downstream end of the radially outer tip of the fixing members proximate the downstream face of the rotor disc, matingly engaging a second blade root of a second one of the blades in a second cone of the slots, the first and second blades circumferentially adjacent to one another, abutting a portion of a rear surface of the second blade root against the sealing tab, and securing the first and second blades to the rotor disc with retaining members.