Failure Studies of a Third Stage Fan Disk from a TF-30Turbine Engine.

摘要

A detailed failure analysis was made of a fan disk from the third stage of the Navy's turbo-jet engine in order to gain a better understanding of the origing and growth kinetics of the cracks that had developed in service. The in service stress that had caused the cracks to originate was determined by a two dimensional photoelastic and holographic stress analysis. A further experimental stress analysis was made to determine the stress intensity factor, after the crack had formed, as a function of crack length. These results were compared with a fractographic study of the bearing surface and the fracture surface. It was found that the striation spacings were in good agreement with the calculated values of the stress intensity factor. Some conclusions were drawn concerning the origin and growth mechanism of these cracks. (Author)