Estimating working life for aircraft gas turbine engine disks at the stage of fatigue crack development. Part 2

It is shown that the cyclic cracking resistance in turbine disk materials is substantially affected by temperature, frequency, loading-cycle shape, and specimen thickness. Formulas describing fatigue crack growth rates are considered and calculations are done on the periods needed for fatigue cracks to grow to critical sizes from stress concentrators at various temperatures. Deceased. Translated from Problemy Prochnosti, No. 12, pp. 3–15, December, 1994.