Failure investigation of 2nd stage compressor disc of an aeroengine.

Second stage compressor rotor discs of a particular type of engines were analyzed. In all the three cases, fatigue cracks were found to have initiated at the rivet-disc interface. No metallurgical abnormalities were found responsible for the fatigue crack initiation and fatigue appeared to be stress related. The most probable reason for fatigue crack initiation appears to be excessive deformation in localized regions on the disc at the rivet contact regions due to high hardness of the rivet material