Patent ID: 8550784

Claim:
In a gas turbine engine rotor comprising a plurality of rotatable blade supporting disks adapted for retention by longitudinal compressive interengagement with one another, at least one disk comprising a medial web and an annular rim disposed at a radially outer portion of said web; said annular rim having longitudinally extending annular shoulders including radially inner and outer annular surfaces thereon; said one disk further including an annular spacer extending longitudinally from said one disk proximal to a juncture of said web and said rim and being spaced radially inwardly from one of said rim shoulders for abutment at a free edge thereof with an adjacent disk for transmission of compressive preloading force and torque transmission between said one disk and said adjacent disk; an airfoil blade cluster comprising a plurality of airfoil rotor blades extending radially outwardly from a segmented annular base; said radially inner surface of said one shoulder of said rim of said one disk and a radially outer surface of said spacer defining in part, a first annular slot, said segmented annular base of said airfoil blade cluster being at least partially received in said first annular slot.