A rotor for a gas turbine engine comprising: a hub defining a central axis of rotation about which the rotor is rotatable in a direction of rotation of the rotor and a plurality of blades radially extending from the hub, the blades being adapted to project into an annular gas flow passage of said gas turbine engine, each of said blades having a remote blade tip defining an outer end surface of the tip, the outer end surface being a radially outermost surface of the blade tip, and a leading edge defined between opposed pressure and suction side airfoil surfaces (48, 50); and a shroud circumferentially surrounding the rotor and having a radially inner surface adjacent to the blade tips, a radial distance between the inner surface of the shroud and the outer end surface of the blades defining a radial tip clearance gap therebetween; a tip leakage flow being formed in the radial tip clearance gap, the tip leakage flow being in a direction opposite to the direction of rotation of the rotor; the tip of each of the blades having a pressure side tip edge formed at a first intersection between the outer end surface and the pressure side airfoil surface, and a suction side tip edge formed at a second intersection between the outer end surface and the suction side airfoil surface, the pressure side tip edge having a first radius of curvature and the suction side tip edge having a second radius of curvature, the second radius of curvature being greater than the first radius of curvature, the suction side tip edge, which has a greater radius of curvature than the pressure side tip edge, thereby reducing the amount of tip leakage flow through the radial tip clearance gap, characterised in that both the first radius of curvature and the second radius of curvature have a center of curvature that is located radially inwardly from the outer end surface of the blade tip. a hub defining a central axis of rotation about which the rotor is rotatable in a direction of rotation of the rotor and a plurality of blades radially extending from the hub, the blades being adapted to project into an annular gas flow passage of said gas turbine engine, each of said blades having a remote blade tip defining an outer end surface of the tip, the outer end surface being a radially outermost surface of the blade tip, and a leading edge defined between opposed pressure and suction side airfoil surfaces (48, 50); and a shroud circumferentially surrounding the rotor and having a radially inner surface adjacent to the blade tips, a radial distance between the inner surface of the shroud and the outer end surface of the blades defining a radial tip clearance gap therebetween; a tip leakage flow being formed in the radial tip clearance gap, the tip leakage flow being in a direction opposite to the direction of rotation of the rotor; the tip of each of the blades having a pressure side tip edge formed at a first intersection between the outer end surface and the pressure side airfoil surface, and a suction side tip edge formed at a second intersection between the outer end surface and the suction side airfoil surface, the pressure side tip edge having a first radius of curvature and the suction side tip edge having a second radius of curvature, the second radius of curvature being greater than the first radius of curvature, the suction side tip edge, which has a greater radius of curvature than the pressure side tip edge, thereby reducing the amount of tip leakage flow through the radial tip clearance gap, characterised in that both the first radius of curvature and the second radius of curvature have a center of curvature that is located radially inwardly from the outer end surface of the blade tip.