| 摘要 |
The invention relates to a turbine rotor for a low pressure turbine of a gas turbine system, in particular of an aero engine, comprising four bladed rotor disks which are arranged in series in the flow direction, wherein at least two of the rotor disks consist at least in part of a nickel-based superalloy which has the following chemical composition: Fe 4%, Co 8.5%, Cr 15.7%, Mo 3.1%, W 2.7%, Al 2.25%, Ti 3.4%, Nb 1.1%, B 0.01%, C 0.015%, Zr 0.03% and remainder Ni. The invention further relates to a low pressure turbine for a gas turbine system, and to a gas turbine system. |
