Fractographic Study of Fatigue Failure of a High-Pressure Turbine Rotor Blade

Abstract

The paper presents the results of a factual study of the fracture surface of a high-pressure turbine rotor blade with a fatigue crack. The study of the fracture relief showed that on the fracture surface of the blade near the trailing edge there is a zone of brittle transcrystalline and intergranular fracture, surrounded by an intragranular fracture with a developed microrelief. Further crack growth in the direction of the leading edge was carried out by a fatigue mechanism. As a result, it was found that the main cause of blade failure is the formation and development of a fatigue crack in the direction from the trailing edge of the airfoil to the leading edge. © 2022 American Institute of Physics Inc.. All rights reserved.