Abstract: A spindle bolt structure is provided in a gas turbine engine. The gas turbine engine includes 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. The spindle bolt structure includes a plurality of spindle bolts extending through the turbine disks and disposed offset from a rotational axis of the turbine disks. The spindle bolts include a first terminal end located adjacent to the compressor side of the turbine disks, and a sleeve member is provided extending over a portion of the first terminal end of each spindle bolt and embedded within a compressor side of the seal disk for effecting a reduction in fretting movement of the spindle bolt relative to the seal disk.

Abstract: A spindle bolt structure is provided in a gas turbine engine. The gas turbine engine includes 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. The spindle bolt structure includes a plurality of spindle bolts extending through the turbine disks and disposed offset from a rotational axis of the turbine disks. The spindle bolts include a first terminal end located adjacent to the compressor side of the turbine disks, and a sleeve member is provided extending over a portion of the first terminal end of each spindle bolt and embedded within a compressor side of the seal disk for effecting a reduction in fretting movement of the spindle bolt relative to the seal disk.

Abstract: A seal strip assembly for use in a turbomachine having a plurality of stages including rotationally driven disks, and arms on opposed portions of adjoining disks to define paired arms with a space therebetween. The seal strip assembly includes a seal strip positioned in the space between the paired arms and having opposing edges for locating in slots formed in opposed faces of the paired arms. An anti-rotation block is provided, where a portion of the anti-rotation block is removably located in opposed openings formed in the paired arms and is engaged with the seal strip to resist movement of the seal strip relative to the paired arms. A detachable engagement member is detachably fastened to the anti-rotation block for maintaining the anti-rotation block in engagement with the seal strip.

Abstract: The turbine includes a plurality of successive stages each having a rotatable disk and blades carried thereby. A pair of adjacent rotatable disks define an annular gap therebetween and have respective opposing sealing band receiving slots aligned with the annular gap. At least one of the rotatable disks has at least one notch therein coupled to the respective sealing band receiving slot, and a sealing band is in the opposing sealing band receiving slots to seal the corresponding annular gap. The sealing band includes at least one sealing strip and at least one movable locking tang carried thereby and extending into the at least one notch to define an anti-rotational feature for the sealing band.

Abstract: A seal strip assembly for use in a turbomachine having a plurality of stages including rotationally driven disks, and arms on opposed portions of adjoining disks to define paired arms with a space therebetween. The seal strip assembly includes a seal strip positioned in the space between the paired arms and having opposing edges for locating in slots formed in opposed faces of the paired arms. An anti-rotation block is provided, where a portion of the anti-rotation block is removably located in opposed openings formed in the paired arms and is engaged with the seal strip to resist movement of the seal strip relative to the paired arms. A detachable engagement member is detachably fastened to the anti-rotation block for maintaining the anti-rotation block in engagement with the seal strip.