Creep fatigue life prediction model and application based on strain energy density dissipation criterion

The key hot-end components represented by aero-engine turbine disks are accompanied by severe creep-fatigue load interaction during service, which has always been a difficult problem in the life design of high-temperature structures. However, the research on creep-fatigue performance prediction of aero-engine high-temperature hot-end components started late in China, and a relatively complete material, theory and method system has not been established, and there is no clearer understanding of the pre-research on structural strength and reliability. Focusing on this problem, this paper explores the creep-fatigue macro-mechanical behavior of domestic nickel-based superalloy GH4169 at 650 ℃ through a large number of experiments, and reveals the load-related creep-fatigue damage mechanism from the micro-scale.