Patent ID: 7874803

Claim:
A gas turbine rotor comprising a rotor disk and turbine rotor blades held in transverse slots provided at the disk periphery, these rotor blades each including an airfoil, a blade platform and a blade root fixed in the respective transverse slot, with the airfoils having cavities flown by cooling air, and with either of opposite side faces of the blade platforms being provided with a recess accommodating a sealing and damping element bridging a gap between the blade platforms, and further comprising at least one air duct connected to at least one cavity in the airfoil which issues on at least one of the side faces of the blade platforms for aerodynamically sealing the gap by supplying an air volume between the blade platforms, wherein the air duct is positioned at a forward end of the blade platform upstream of 1) a leading edge of the airfoil and 2) the sealing and damping element, to aerodynamically seal the gap between forward ends of the blade platforms.