Abstract
The paper considers procedures for predicting safe damage to compressor and turbine disks in stationary and aircraft gas turbine engines at the stage of subcritical crack growth. The methods are proposed to evaluate inspection intervals and amounts of routine maintenance with consideration of the regularities underlying this type of crack growth. In this case, the features in the operation of materials are taken into consideration for stationary (peaking, semi-peaking, and steady-state modes) and aircraft (typical flight cycles) gas turbine engines. The crack propagation near various stress concentrators is analyzed with the help of the developed program using a stationary gas turbine disk as an example, which allows one to predict the crack growth life of the disk and the most probable location of its failure.
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