• Gas-turbine engine generates thrust by jet propulsion

  • Turbine blades of aircraft engine are responsible for 50%-75% of thrust

  • The high-cycle fatigue (HCF) of the turbine blades and other engine components has traditionally been analyzed with Goodman diagram

  • However, increasing incidence of late of the HCF-related engine failures calls for new approaches

  • Peridynamic modeling can depict the damage mechanisms and identify critical regions of turbine blade susceptible to damage

  • Prescribed Force has lift and drag components 

  • Damage resulting from fatigue of blade had a strong dependence on the number of cycles

  • Damage peaked at the bottom of the trailing edge of the blade

  • It is likely that cracks would form in this area at a larger number of cycles

  • There was also some damage accumulated at the blade/disk interface

  • Credit/acknowledgement: The turbine blades geometry is the courtesy of the GrabCAD (https://grabcad.com/library) library

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