Patent ID: 7926260

Claim:
A shaft for a gas turbine engine, comprising: a first shaft section, extending between a forward axial end and an aft axial end along a first axial centerline; a second shaft section, extending between a forward axial end and an aft axial end along a second axial centerline; a first flexible linkage including a bridge section connected between a first diaphragm and a second diaphragm, which first diaphragm is connected to the aft axial end of the first shaft section, and which second diaphragm is connected to the forward axial end of the second shaft section; and a second flexible linkage including a diaphragm and a hub, which diaphragm cantilevers radially outwardly from an inner radial end to an outer radial end and is connected to the aft axial end of the second shaft section, and which hub is connected to the outer radial end of the second flexible linkage diaphragm, and includes an engine shaft coupling connected to the hub.