Research on creep performance evaluation method of single crystal turbine blades based on crystal plastic slip theory

Crystal plastic slip and microstructural evolution are the primary mechanisms governing creep failure in single-crystal superalloys. Based on these failure characteristics, this paper focuses on the engineering application and full‑chain implementation of creep performance evaluation technology for full‑scale single‑crystal turbine blades based on material micromechanical behavior, establishing the engineering practical application system of this micromechanical model to full‑scale single‑crystal turbine blades. First, a dual-damage-parameter creep constitutive model considering crystal slip is adopted, and its temperature-dependent parameters are accurately calibrated via a genetic algorithm based on creep test data covering the actual service temperature range of turbine blades. Second, a creep UMAT subroutine is developed for finite element simulation of full-scale nickel-based single-crystal high-pressure turbine blades. Third, the accuracy of the creep life evaluation method is verified using standard creep test data of smooth blade regions. This work realizes the engineering application of the micromechanical creep model to full-scale single-crystal turbine blades, forms a full-chain technical system including multi-temperature creep testing, temperature-dependent parameter calibration, and full-component life verification, and provides a practical approach for the structural integrity assessment of aero-engine components.