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A damage coupled elastic-plastic constitutive model and its application on low cycle fatigue life prediction of turbine blade

机译:损伤耦合弹塑性本构模型及其在涡轮叶片低周疲劳寿命预测中的应用

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摘要

Based on continuum damage mechanics (CDM), a damage coupled elastic-plastic constitutive model combined with multilinear hardening relation is proposed and applied on low cycle fatigue (LCF) life prediction of turbine blade. The model has considered the local rigidity attenuation of structure caused by fatigue damage in elastic and plastic stage, and it is implemented combining with finite element method (FEM) to predict the crack initiation lives of turbine blades. Runge-Kutta (RK) method is employed in the solving process of damage accumulation. By conducting the calculation in several time step sizes, the convergence of the proposed model is examined. To validate the predicted results, groups of LCF experiments are conducted on full-scale turbine blades. The macroscopic fracture shows that the crack initiation region is in accordance with the predicted results. Compared with the experimental results, the predicted lives of the proposed model, an existing CDM model without coupling with constitutive relation and Morrow model are within factors of 2.31, 3.93 and 9.15 in scatter band respectively, indicating the high accuracy of the proposed model. Expect for turbine blades, the proposed model can be used to predict the LCF lives of other structures.
机译:基于连续损伤力学(CDM),提出了一种结合多线性硬化关系的损伤耦合弹塑性本构模型,并将其应用于涡轮叶片的低周疲劳寿命预测中。该模型考虑了弹塑性阶段疲劳损伤引起的结构局部刚度衰减,并结合有限元方法(FEM)进行了预测,预测了涡轮叶片的裂纹萌生寿命。 Runge-Kutta(RK)方法用于解决损伤累积的过程。通过以几个时间步长进行计算,可以检验所提出模型的收敛性。为了验证预测结果,在大型涡轮机叶片上进行了LCF实验组。宏观断裂表明裂纹萌生区域与预测结果一致。与实验结果相比,该模型的预测寿命,不存在本构关系的CDM模型和Morrow模型的离散寿命分别在2.31、3.93和9.15倍以内,表明该模型具有较高的精度。对于涡轮机叶片,所建议的模型可用于预测其他结构的LCF寿命。

著录项

  • 来源
    《International Journal of Fatigue》 |2020年第2期|105298.1-105298.12|共12页
  • 作者单位

    School of Energy and Power Engineering Beihang University Beijing 100191 China;

    School of Energy and Power Engineering Beihang University Beijing 100191 China Collaborative Innovation Center of Advanced Aero-Engine Beijing 100191 China National Key Laboratory of Science and Technology on Aero-Engine Aero-mermodynamics Beijing 100191 China Beijing Key Laboratory of Aero-Engine Structure and Strength Beijing 100191 China;

    School of Energy and Power Engineering Beihang University Beijing 100191 China Collaborative Innovation Center of Advanced Aero-Engine Beijing 100191 China Beijing Key Laboratory of Aero-Engine Structure and Strength Beijing 100191 China;

    Army Aviation Institution Army Aviation School Beijing 100121 China;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

    Continuum damage mechanics; Elastic-plastic constitutive model; Low cycle fatigue; Life prediction; Turbine blade;

    机译:连续损伤力学;弹塑性本构模型低周疲劳;寿命预测;涡轮叶片;

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