Rotors for a gas turbine engine, corresponding gas turbine engine and method

A rotor (24) for a gas turbine engine includes a plurality of radially extending blades (28), each having a remote blade tip (30) defining an outer tip surface, and a leading edge (46) defined between opposed pressure and suction side airfoil surfaces (48, 50). A shroud (32) circumferentially surrounds the rotor (24), and a radial distance between an inner surface of the shroud (34) and the outer tip surface of the blades (28) defines a radial tip clearance gap (54) therebetween. The tip (30) of each of the blades (28) has a pressure side edge (62) formed at the intersection between the outer tip surface and the pressure side airfoil surface (48), and a suction side edge (60) formed at the intersection between the outer tip surface and the suction side airfoil surface (48). The suction side edge (60) has a larger radius of curvature than the pressure side edge (62), thereby reducing the amount of tip leakage flow through the radial tip clearance gap.