Creep-fatigue life prediction method and experimental validation of nickel-based superalloy DZ125
SUN Debin
MA Yumeng
GAO Kun
MA Changliang
Abstract：The creep-fatigue damage generated by turbine blades serving in the"3H"(High temperature,High pressure,High speed)environment affects the safe operation of aircraft engines.Aiming at the creep-fatigue damage failure of aircraft engine turbine blades,based on the Kachanov-Rabotnov-Lemaitre damage mechanics method,the mean stress to temperature ratio parameter is introduced to construct a creep-fatigue life prediction model for turbine blade material nickel-based superalloy DZ125.The model is verified through creep fatigue tests conducted in the laboratory.Research has shown that the constructed creep-fatigue life prediction model has high life prediction accuracy,with prediction results located within a 1.5-fold dispersion band.The above research proposes a creep-fatigue life prediction method for turbine blade materials in the"3H"environment,providing a theoretical basis for accurately predicting the structural life and having important engineering application value.
Keywords："3H" environmentturbine bladeDZ125creep-fatiguelife prediction
Publication Date：2025-07-20
Online Publishing Date：2025-09-08(First online date of this platform, not the publication date of the document)
Pages：5( 73-77 )