Siemens Energy, Inc.

David M Shaefer

Kevin Michael Light

Manish S Gurao

Brian D Nereim

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.

Gas turbine spindle bolt structure with reduced fretting motion

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.

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Chuluota, FL, United States of America

David M Shaefer