| 摘要 |
The invention relates to a gas turbine (20) of the axial flow type, comprising a rotor (13) and a stator, which stator constitutes a casing surrounding the rotor (13), thereby providing a hot gas path, through which hot gas formed in a combustion chamber passes, whereby the rotor (13) comprises a rotor shaft (15) with axial slots, especially of the fir-tree type, for receiving a plurality of blades (B1-B3), which are arranged in a series of blade rows, with rotor heat shields (R1, R2) interposed between adjacent blade rows, thereby forming an inner outline of the hot gas path, and whereby the rotor shaft (15) is configured to conduct a main flow of cooling air (17) in axial direction along the rotor heat shields (R1, R2) and the lower parts of the blades (B1-B3), and whereby the rotor shaft (15) supplies the blades (B1-B3) with cooling air (18) entering the interior of the blades (B1-B3). 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). |
