Rotor of a turbine of a gas turbine with improved cooling air routing

Rotor of a turbine of a gas turbine having a turbine rotor hub, on which over the circumference a plurality of blade platforms is arranged, each of which carrying at least one turbine blade, and having one each cooling air chamber for passing through cooling air formed by adjacent blade platforms and a damping element and/or a sealing element, where between adjacent blade platforms at least one damping element and/or sealing element is arranged radially beneath a platform intermediate gap provided between adjacent blade platforms, wherein the resultant cooling air chamber and/or the platform intermediate gap are designed such that starting from a side of the blade platform facing the adjacent blade platform, at least one outflow pocket open to the platform upper side and connected to the cooling air chamber is formed, and that at least one cooling air pocket opened radially inwards to the cooling air chamber is provided in the wall of the cooling air chamber and opens towards the damping element and/or the sealing element or the platform intermediate gap.