Patent ID: 8579538

Claim:
A gas turbine engine comprising: a fan disposed about an axis; a compressor section axially aft of the fan and arranged to receive air flow from the fan; a combustion section axially aft of the compressor section and fluidly connected to the compressor section; a turbine section connected to the compressor section and arranged to drive the compressor section; and a coupling stack through which the turbine section drives the compressor section, the coupling stack comprising an input coupling connected to the fan; a tie-bolt; a plurality of aligned slots defined in the input coupling and the tie-bolt; and a tab lock having an annular body with an axial front side and an axial back side, the annular body including a plurality of openings extending into a radial inner periphery of the annular body, a plurality of flanges on the axial back side of the annular body adjacent to the plurality of openings, and a plurality of tabs, at least a portion of each tab inserted into one of the plurality of aligned slots.