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 ; 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 ; 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 . <EOS>