GAS TURBINE AND CORRESPONDING LAST ROTOR DISK

A gas turbine comprises a rotor made of a plurality of rotor disks adjacent arranged along the rotor axis and shaped for realizing cavities between the respectively adjacent disks. The rotor comprisesa last rotor disk and has a downstream portion for supporting a bearing cover and an upstream portion for supporting a last turbine blade. The gas turbine is provided with a cooling duct system configured for supplying cooling air from a downstream end of the turbine section to the last turbine blade passing inside the last rotor disk. The cooling duct system comprises an axial bore in the downstream portion of the last rotor disk along the rotor axis and a first plurality of inclined radial bores in the upstream portion of the last rotor disk off the axis. 燃气涡轮包括：压缩机区段，设置有用于压缩空气压缩机叶片和导叶；燃烧区段，用于压缩且燃烧空气和燃料的混合物；涡轮区段，设置有使燃烧后的混合物膨胀的涡轮叶片和导叶；燃气涡轮包括转子，其具有轴，且从压缩机区段延伸至涡轮区段，以便支撑压缩机和涡轮叶片；转子由多个转子盘构成，其相邻布置且成形为在相邻的盘之间实现腔；转子包括具有用于下游部分和上游部分的最后个转子盘；燃气涡轮设置有冷却导管系统，配置成用于将冷却空气从涡轮区段的下游端经过最后个转子盘内侧供应至最后个涡轮叶片；冷却导管系统包括：沿着转子轴的最后个转子盘的下游部分中的