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<p>Aircraft engines are the core propulsion equipment of aircraft, and their operational performance and service life directly determine the motion capability of the aircraft. To conduct a detailed analysis of the working performance of aircraft engines, this study designs a combustion chamber life prediction technology for aircraft engines based on crack propagation behavior. The first-stage creep rate is determined by calculating the difference between the total creep rate and the second-stage creep rate during the process. Damaged materials are considered as macroscopic homogeneous bodies, and crack characteristics are analyzed by calculating stress, strain, and damage state. Simplified quarter compact tensile specimens are selected for finite element analysis. The experiment showed that when calculating crack propagation and damage proportion, the research method maintained the lowest accuracy of damage proportion calculation at 98.2% or above. When analyzing the equivalent stress situation in the crack discontinuity area, it was found that when the main crack length was 0.1&#xa0;mm, the equivalent stress at the tip corresponding to an initial crack depth ratio of 0.45 was 507&#xa0;MPa. In the analysis of equivalent stress changes, the maximum equivalent stress when the crack was 0.1&#xa0;mm was 366&#xa0;MPa. The research method can effectively predict the lifespan of aviation engine combustion chambers and has high accuracy.</p>

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Construction of Finite Element Damage Model and Life Prediction of Compact Tensile Specimens in Aircraft Engine Combustion Chamber under Creep–Fatigue Interaction

  • 期刊论文

  • 发表日期：

    2026年3月18日

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  • Wei Fu,
  • Haixin Wang,
  • Xiaohui Sun,
  • Zongxian Song,
  • Shuqing Xu,
  • Miaojia Xu,
  • Lijuan Liu,
  • N. A. Razak

摘要

Aircraft engines are the core propulsion equipment of aircraft, and their operational performance and service life directly determine the motion capability of the aircraft. To conduct a detailed analysis of the working performance of aircraft engines, this study designs a combustion chamber life prediction technology for aircraft engines based on crack propagation behavior. The first-stage creep rate is determined by calculating the difference between the total creep rate and the second-stage creep rate during the process. Damaged materials are considered as macroscopic homogeneous bodies, and crack characteristics are analyzed by calculating stress, strain, and damage state. Simplified quarter compact tensile specimens are selected for finite element analysis. The experiment showed that when calculating crack propagation and damage proportion, the research method maintained the lowest accuracy of damage proportion calculation at 98.2% or above. When analyzing the equivalent stress situation in the crack discontinuity area, it was found that when the main crack length was 0.1 mm, the equivalent stress at the tip corresponding to an initial crack depth ratio of 0.45 was 507 MPa. In the analysis of equivalent stress changes, the maximum equivalent stress when the crack was 0.1 mm was 366 MPa. The research method can effectively predict the lifespan of aviation engine combustion chambers and has high accuracy.