Patent ID: 8608436

Claim:
A gas turbine engine rotor assembly comprising: first and second rotor components circumscribing a centerline axis, the first rotor component including an annular sleeve on the first rotor component, an annular tapered conical slot extending axially inwardly into the sleeve from an annular opening of the slot, the tapered conical slot tapering axially into the sleeve from the opening, the sleeve including a sleeve inner conical surface in part bounding the conical slot, the second rotor component including an annular rim received within the conical slot, the annular rim including a rim inner conical surface mating with and pressing against the sleeve inner conical surface, a sleeve cylindrical outer surface in part bounding the conical slot in the sleeve, a rim outer cylindrical surface on the annular rim, and the annular rim outer cylindrical surface mating with and contacting the sleeve cylindrical outer surface.