Patent attributes
An axial flow gas turbine (20) includes a rotor (13) and a stator, and a hot gas path through which hot gas passes. The rotor (13) includes a rotor shaft (15) with axial slots for receiving a plurality of blades (B1-B3) arranged in a series of blade rows, with rotor heat shields (R1, R2) interposed between adjacent blade rows. The rotor shaft (15) is configured to axially conduct a main flow of cooling air along the rotor heat shields (R1, R2) and the lower parts of the blades (B1-B3), and the rotor shaft (15) supplies the interior of the blades (B1-B3) with cooling air (18). Stable and predictable cooling air parameters at any blade row inlet are secured by providing air-tight cooling channels (21), which extend axially through the rotor shaft (15) separate from the main flow of cooling air (17), and supply the blades (B1-B3) with cooling air (18).
