• 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