Abstract
The cracking problem of aviation unit part under the influence of the thermal pulse loading were considered. The problem of thermal plasticity during thermal pulse processing were solved in CAE system Ansys; internal stresses were calculated and stress concentration zones in the part were defined. A numerical simulation of crack formation in the zone of greatest stress concentration allowed to determine the stress intensity factors for the case of normal separation, transverse and longitudinal shift and J-integral. This study allows to estimate the defect behavior during thermal pulse part treatment. The reliability of obtained results is confirmed by the adequacy of used models. In subsequently the study of metal fracture toughness allows to improve the method of setting modes for thermal pulse parts treatment taking into account the strength limit.
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