Patent ID: 7568886

Claim:
A rotor for a turbo-machine, comprising: a rotor disk inspection area arranged on a low stress portion of the rotor that is visually inspectable; a failure site arranged in the inspection area formed essentially as a notch such that the failure site is representative of a non-inspectable critical stress location of the rotor; and a hole arranged at a predetermined distance from the failure site such that the hole limits the length of a crack that initiates at the failure site, wherein the failure site is formed on an annular platform of the rotor such that circumferential loads of the rotor operatively act upon the failure site, wherein the rotor comprises a plurality of rotor disks and a tension bolt clamping the rotor disks, wherein the rotor is a single piece rotor, wherein the rotor is welded, wherein the failure site is arranged on an end face of one of the plurality of rotor disks, and wherein the rotor has a plurality of failure sites distributed on a rotor disk and the failure sites are formed differently to identify different stress levels of the rotor and a comparable crack propagation analysis.