Patent ID: 6808362
Filing Date: 2004-10-26
Classification: F01D,F04D

Abstract:
A rotor for a gas turbine, which rotor comprises a plurality of rotor disks arranged one behind the other in a rotor axis and connected to one another, and which rotor extends between a compressor part and a turbine part and has a central bore running between said compressor part and said turbine part and having an inside diameter, there being first passage means branching off cooling air in the compressor part and directing it radially inward through the rotor into the central bore, and second passage means which, in the turbine part, for direct the cooling air from the central bore radially outward through the rotor, wherein the first passage means comprise a plurality of first radial bores, which first radial bores run from the outside to the inside through a first rotor disk and open into a first annular cavity arranged in this first rotor disk concentrically to the rotor axis, said first cavity is connected to the central bore, in that the said first cavity has an outside diameter which is greater than the inside diameter of the central bore, and in that the first cavity is subdivided into individual chambers by a plurality of radially arranged first ribs, and wherein all the first radial bores have the same bore diameter, and the outside diameter of the first cavity is selected in such a way that the distance between two adjacent first radial bores at the orifice to the first cavity corresponds approximately to the bore diameter.