CRACK INITIATION OF ROTOR BLADES IN THE FIRST STAGE OF SO-3 COMPRESSOR

摘要

The failure of rotor blades in the first stage of a SO-3 engine was observed during an experiment in a test rig. The rotating mode shapes of flexible blade and bladed disc assemblies were calculated. A Campbell diagram was presented to find the areas where resonances may have occurred. Numerical calculations were used to locate the crack initiations. When blocks were placed in the stator blades (to simulate the effect of birds getting into the engine), it took approximately 143 minutes of operating time for an initial crack of 3 mm to appear on the pressure side.