| 摘要 |
A gas turbine rotor (5) is provided with a longitudinal stack of blade supporting disks (10,15,20) each including a medial web (35) and a radially outer rim (75,40). The disks (10,15,20) are spaced from one another by axial gaps (42). The disks (10,15,20) include recesses (80,85) in the forward and aft major surfaces thereof proximal to the juncture of the webs (35) and rims (75,40) thereof. Annular spacers (90) received with the recesses (80,85) in the disks (10,15,20) span the axial gaps (42) and provide a load path for the axial compressive preloading of the disks (10,15,20) and the transmission of torque along the disk stack. |
