Research on high-low cycle fatigue damage of aircraft engine blades based on numerical simulation

In response to the complex alternating loads that aircraft engine blades endure and their vulnerability to fatigue damage, a study was undertaken to investigate high-low cycle composite fatigue damage through numerical simulation. The initial phase of the research involved analyzing the characteristics of high-low cycle composite fatigue loading, which encompassed uncertainties, load histories, and variations in geometric parameters. This analysis aimed to elucidate the behaviors and damage mechanisms of the blades. Subsequently, the study applied continuum damage mechanics to explore the interplay between high-cycle fatigue and low-cycle fatigue, including their combined effects. This theoretical exploration resulted in the development of a constitutive equation specifically for high-low cycle composite fatigue damage in engine blades. Additionally, a finite element model for aircraft engine blades was constructed, facilitating both static and dynamic analyse s through finite element analysis software. This model allowed for the assessment of stress field distribution and vibration characteristics under various operational conditions. These insights offer critical theoretical support and methodological guidance for enhancing the design and extending the lifespan of aircraft engine blades, thereby improving engine safety and reliability.