An investigation on fatigue of turbine blades of aircraft engine by high cycles fatigue test

Thermal stress, wear and material damage produce effects of high-cycle fatigue failures in aircraft engines. The loading configuration on turbine blades of aircraft engines consists of an axial load. The axial load is the centrifugal force combined with the tensile and compressive loads, caused by the natural vibrations of the blades themselves. Low-cycle fatigue and high-cycle fatigue loading tests simulate these flight loads experienced by engine components. The objective of this study is to illustrate the most important features of high-cycle fatigue to pass the final controls for the assurance of quality of turbine blades in aircraft engines. A finite element model, useful to predict the results of experimental tests, is also presented.