Patent ID: 8152471

Claim:
An apparatus for retaining bladed rotor disks in a jet engine which includes an axial-flow compressor having a plurality of bladed rotor disks, with at least two bladed rotor disks at a compressor inlet side being designed as blisks where each blisk integrally combines a rotor disk and circumferentially distributed rotor blades; at least one turbine section; and at least one shaft interconnecting the compressor and turbine section; comprising: at least one tie-rod, releasably retaining the blisks to one of the rotor disks disposed immediately downstream of the blisks while other rotor disks are firmly attached to each other and the one of the rotor disks separately and independently of the tie-rod such that the blisks can be separated from the rotor disks while the rotor disks remain attached to one another; wherein the tie-rod is essentially tubular, coaxial with an axis of the compressor, disposed within central apertures in the blisks and firmly attached to the shaft; wherein the tie rod includes at least one first arrangement disposed upstream of the blisks and at least one second arrangement disposed downstream of the blisks and connected to the one rotor disk disposed immediately downstream of the blisks and the blisks are retained via the tie rod between the first arrangement and the second arrangement.