-
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