Well, it most likely would be a high-cycle fatigue failure. The turbine wheels are spun to 110% of maximum allowable rpm both as a check of the assembled wheel and to set up residual compressive stresses in the turbine blades to significantly lower the maximum tensile stresses during operation. There could have been a material flaw at the molecular level that, over time, could have grown to its critical crack length causing the turbine blade to release. Given that the released turbine blade was contained is testament to the design of the engine, considering that in the turbine section the temperatures are in excess of 1500 degrees in places and the turbine wheels are spinning at 30,000rpm, it could have been catastrophic (loss of aircraft) had the design not been able to contain the released blade assembly.