| 摘要 |
A rotor (60) for a gas turbine engine includes a plurality of blades (62) which extend from a rotor disk (66). One or more cooling features (90) may be incorporated radially inboard from the rotor disk rim (70) that operate to induce vortices adjacent to the disk rim (70) and/or disk web (72). The vortices increase the local velocity in the secondary cooling air flow path and therefore increase the heat transfer rate from the rotor (60) to the secondary cooling air flow path. |
