The invention relates to an aero-engine
stator part crack
critical dimension comprehensive determination method and
system, and belongs to the technical field of
aviation, the method comprises the following steps: obtaining an aero-engine typical hot end
stator part geometric model and material parameters, and carrying out
static strength analysis according to fluid-thermal-
solid coupling load characteristics in actual working conditions; inserting an initial crack into a first
principal stress plane of a dangerous part of the real component, carrying out crack propagation
simulation to determine a crack propagation path, and calculating a critical
crack size of a dangerous point; analyzing critical crack sizes under different failure
modes, such as cooling failure and buckling failure; and integrating analysis results under the multi-failure mode, and determining a comprehensive
critical dimension as a final judgment standard. According to the method, through combination of
fracture failure and function
failure analysis, accurate judgment of the
critical dimension of the crack is realized, limitation of a traditional single fracture criterion is broken through, comprehensive function
failure analysis is realized, the accuracy of a maintenance decision is remarkably improved, and a scientific basis is provided for condition-based maintenance decision.