Kinetics and Mechanisms of Degradation of the Surface Layers of Gas-Turbine Engine Structural Components Under Cyclic Thermal Loading During Initiation and Propagation of Thermal Fatigue Cracks

Studies of surface layer material degradation of the most loaded elements of gas turbine engine structural components revealed the essential changes in the structure and elemental composition of this layer in the thermal fatigue crack initiation zones, as well as along the propagating crack lips. The intensity of the observed changes implies the necessity of their account in the stress-strain state calculations and residual life estimations of high-temperature structural components of gas turbine engines.