Understanding progressive failure mechanisms of a wind turbine blade trailing edge section through subcomponent tests and nonlinear FE analysis
Understanding progressive failure mechanisms of a wind turbine blade trailing edge section through subcomponent tests and nonlinear FE analysis
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DOI：
10.1016/j.compstruct.2019.02.024
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发表时间：
2019-04
影响因子：
6.3
通讯作者：
Xiao Chen;P. Berring;S. H. Madsen;K. Branner;S. Semenov
中科院分区：
文献类型：
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作者：
Xiao Chen;P. Berring;S. H. Madsen;K. Branner;S. Semenov
本文对复合材料风力机叶片尾缘截面的结构破坏进行了全面的研究。重点在于了解子元件测试中后缘部分在其整个失效序列中的渐进失效行为。用数字图像相关法(DIC)测量了试件的屈曲变形和应变分布。执行详细的试验后检查，以确定故障模式和故障特征。基于连续损伤力学和渐进破坏分析技术，建立了考虑所有破坏模式的非线性有限元模型。该模型考虑了由于屈曲、接触和材料失效引起的多种结构非线性，以预测结构的失效过程。研究表明，除了屈曲驱动的破坏现象外，夹层板的表面接触对后缘截面的破坏过程也有贡献。泡沫材料在达到试件的极限承载能力之前就开始失效，而复合材料和粘结材料都在峰值后失效。复合材料层合板的破坏发生在纤维为主的破坏之前，先发生基体为主的破坏和分层。所提出的有限元模型较好地模拟了后缘截面的渐进破坏过程。
This paper presents a comprehensive study on structural failure of a trailing edge section cut from a composite wind turbine blade. The focus is placed on understanding progressive failure behavior of the trailing edge section in subcomponent testing during its entire failure sequence. Digital Image Correlation (DIC) is used to capture buckling deformation and strain distributions of the specimen. Detailed post-test inspection is performed to identify failure modes and failure characteristics. A nonlinear Finite Element (FE) model that accounts for all observed failure modes is developed based on continuum damage mechanics and progressive failure analysis techniques. Multiple structural nonlinearities due to buckling, contact and material failures are included in the model to predict the failure process. The study shows that in addition to the buckling-driven failure phenomenon, the surface contact of sandwich panels contributes to the failure process of the trailing edge section. Foam materials start to fail before the ultimate load-carrying capacity of the specimen is reached, while both composite materials and adhesive materials fail in the post-peak regime. The matrix-dominant failure and delamination develop before the fiber-dominant failure in composite laminates. The proposed FE model captures the progressive failure process of the trailing edge section reasonably well.