Patent ID: 8388303

Claim:
A gas turbine comprising: a rotor including a turbine rotor, a shaft and a compressor rotor, the turbine rotor having at least one bladed rotor disk and a rotor cone leading from the at least one rotor disk to the shaft, a downstream end of the shaft being rotatably supported in a bearing having a bearing chamber, an interior space of the shaft being designed as a flow channel for sealing air leading to the bearing chamber, and a space surrounding the rotor cone upstream of the rotor cone being designed as a flow space for cooling air used for cooling the rotor blades, wherein, in a region of a connection of the rotor cone, the shaft has an expanded portion having an enlarged inside and outside diameter, and at an upstream end of the expanded portion, openings are provided to allow the cooling air to enter into an expanded interior space of the shaft and, at a downstream end of the expanded portion, other openings are provided to allow the cooling air to exit into a further space between the bearing chamber and the rotor cone, the expanded interior space being sealed from the a further interior space of the shaft by a wall for separating the cooling air and the sealing air, wherein the expanded portion is integrally formed with the downstream end of the shaft.