Gas turbine spindle bolt structure with reduced fretting motion

In a gas turbine engine a rotor including a plurality of turbine disks for supporting rows of blades, a torque tube located on a compressor side of the turbine disks, and a seal disk located between the torque tube and a first stage turbine disk, a spindle bolt structure comprising:

• spindle bolts extending through the turbine disks, the spindle bolts being disposed circumferentially around and offset from a rotational axis of the turbine disks;
• the spindle bolts including a first terminal end located adjacent to the compressor side of the turbine disks;
• a plurality of holes in the seal disk aligned with corresponding holes in the turbine disks for receiving the spindle bolts, each hole in the seal disk comprising a stepped portion defining a shoulder between opposing axial faces of the seal disk;
• a sleeve member extending over a portion of the first terminal end of each of the spindle bolts and embedded within a compressor side of the seal disk;
• and
• each of the sleeve members including an engagement end engaged on a shoulder within a respective hole in the seal disk for effecting a reduction in fretting movement of the spindle bolt relative to the seal disk.