| 摘要 |
A gas turbine disk assembly includes a rotor (2) and a tie-bolt (50). The rotor (2) includes a plurality of blades (22) and a plurality of disks (210). The plurality of blades (22) is disposed on outer circumferential surfaces of the plurality of disks (120). The tie-bolt (50) is disposed along a center axis of the rotor (2) and through a bore (70) defined through hollow portions of the plurality of disks (210), so as to couple the plurality of disks (210) to each other. A diameter of the bore (70) is larger than a diameter of the tie-bolt (50). The plurality of disks (210) respectively include a groove (71) spaced from the bore (70) in the circumferential direction of the bore (70), the groove (71) being elongated in the axial direction of the bore (70) such that cooling air flows through an internal space thereof. |
