Scholarlink

<p>Fretting fatigue in bolted joints within aero-engine fan and compressor structures, characterized by multi-layered, thin-walled components and high preload, poses a significant structural safety challenge. This study investigates fretting fatigue in a bolted joint configuration simulating compressor axis contact with sealing disk ends, analyzing hysteresis loops, fretting scars, and fracture surfaces. Numerical simulation, incorporating a UMESHMOTION subroutine, and a critical plane approach utilizing the Smith-Watson-Thorpe parameter and Miner’s law, alongside wear morphology simulation, were employed to evaluate fretting fatigue life. Results revealed a non-monotonic relationship between surface quality and fretting fatigue life, demonstrating an initial life decrease followed by an increase, primarily due to a transition from partial to gross slip. The study highlights the significant impact of fretting on the life prediction of aero-engine bolted joints, demonstrating that improved surface quality does not always guarantee enhanced fatigue performance. The accuracy of the life prediction approach was validated through experimental correlation with wear-aware simulation results.</p>

错误：搜索内容不能为空，请输入英文关键词
错误：关键词超出字数限制，请精简
高级检索

Fretting Fatigue Behavior of Ti-6Al-4V Alloy Bolted Joints with Bolted Connection Features in Aero-engines

  • 期刊论文

  • 发表日期：

    2025年7月8日

查看全文
  • Chen Wang,
  • Yibo Shang,
  • Yue Su,
  • Liucheng Zhou,
  • Weifeng He,
  • Bin Li

摘要

Fretting fatigue in bolted joints within aero-engine fan and compressor structures, characterized by multi-layered, thin-walled components and high preload, poses a significant structural safety challenge. This study investigates fretting fatigue in a bolted joint configuration simulating compressor axis contact with sealing disk ends, analyzing hysteresis loops, fretting scars, and fracture surfaces. Numerical simulation, incorporating a UMESHMOTION subroutine, and a critical plane approach utilizing the Smith-Watson-Thorpe parameter and Miner’s law, alongside wear morphology simulation, were employed to evaluate fretting fatigue life. Results revealed a non-monotonic relationship between surface quality and fretting fatigue life, demonstrating an initial life decrease followed by an increase, primarily due to a transition from partial to gross slip. The study highlights the significant impact of fretting on the life prediction of aero-engine bolted joints, demonstrating that improved surface quality does not always guarantee enhanced fatigue performance. The accuracy of the life prediction approach was validated through experimental correlation with wear-aware simulation results.