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FEM-DBEM approach to simulate crack propagation in a turbine vane segment undergoing a fatigue load spectrum

机译：模拟疲劳负载谱中涡轮叶片段中裂纹传播的FEM-DBEM方法

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摘要

In this work a thermo-mechanical fatigue application, related to a crack propagation in an aircraft turbine vane undergoing a complex load spectrum, is simulated. A computationally efficient FEM-DBEM submodelling approach, whose implementation leverages on the principle of linear superposition, is adopted. When tackling a crack propagation problem with a FEM-DBEM combined approach, the global analysis is generally worked out by FEM whereas the fracture problem is solved in a DBEM environment. In particular, a DBEM submodel is extracted from the global uncracked FEM model and, generally, is loaded on the boundaries with temperatures and either displacements or tractions; then the crack propagation is simulated by repeated thermal-stress DBEM analyses. Differently from that, the proposed equivalent approach solves the crack propagation problem by adopting a simpler pure stress DBEM analyses in which the boundary conditions, in terms of tractions, are just needed on the DBEM crack faces. Such tractions are evaluated by the FEM global analysis along a virtual surface traced by the advancing crack (the FEM model is uncracked). Such an approach provides accuracy enhancement and computational advantages.
机译：在该工作中，模拟了经历复杂负载谱的飞机涡轮叶片中的裂纹传播的热机械疲劳应用。采用了计算上的有效的FEM-DBEM模拟方法，其实现利用线性叠加原理的利用。在用FEM-DBEM组合方法解决裂缝传播问题时，全局分析通常由FEM工作，而裂缝问题在DBEM环境中得到解决。特别地，从全局未填充的有限元模型中提取DBEM子模型，通常，在温度和位移或牵引的边界上装载在边界上;然后通过重复的热应力DBEM分析模拟裂缝扩展。与之不同，所提出的等效方法通过采用更简单的纯应力DBEM分析来解决裂缝传播问题，其中在牵引力方面仅在DBEM裂纹面上需要边界条件。通过沿着推进裂缝描绘的虚拟表面的FEM全局分析来评估这种诉讼（有组织模型未触发）。这种方法提供准确性的增强和计算优势。

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