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Simplified Method to Predict Elastic-Plastic Behaviour of Aeroengine Casings

机译：航空发动机机壳弹塑性行为的简化预测方法

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The assessment of elastic-plastic damage and residual deformations in complex aeroengine casing structures is an important issue for structural integrity and safety. The availability of computational methods for prediction of the elastic-plastic behaviour of components and structures gives an opportunity for significant new insight and thus more optimised design. However, the complexity of typical casing geometries makes routine non-linear analyses expensive, both in terms of model development and analysis run-times. This paper is therefore concerned with the development of simplified but accurate methods for non-linear casing analyses. A simplified aeroengine casing structure is considered characterised by features such as a thin outer shell with flanges, a thick inner hub and solid radial spokes connecting the latter to the former. Typical aeroengine casings may experience axial force, bending moment and radial loading due to shaft bearings and attention is focussed here on static loading, including overload conditions due to an extreme event, such as the fan blade-off condition (FBO). The repeated local joints at the spoke-shell casing junctions are of particular interest as the most likely sites for plastic deformation and possibly crack initiation. Analogy with previous work on prediction of elastic-plastic force-displacement responses in isolated tubular joints has suggested the possibility of employing a similar technique. Therefore, a prediction procedure has been developed for the spoke to outer shell connection behaviour based on complementary energy level curves in the two-dimensional loadspace of spoke axial loads and bending moments.
机译：对于复杂的航空发动机壳体结构，弹塑性损伤和残余变形的评估是结构完整性和安全性的重要问题。预测部件和结构的弹塑性行为的计算方法的可用性为重要的新见识提供了机会，从而可以进行更优化的设计。但是，典型的套管几何形状的复杂性使得常规的非线性分析在模型开发和分析运行时间方面都变得昂贵。因此，本文涉及非线性套管分析的简化但准确的方法的发展。考虑到一种简化的航空发动机壳体结构，其特征在于诸如具有凸缘的薄外壳，较厚的内毂和将后者与前者连接的坚固的径向辐条。典型的航空发动机机壳可能会由于轴轴承而承受轴向力，弯矩和径向载荷，此处的注意力集中在静态载荷上，包括由于极端事件而导致的过载条件，例如风扇叶片脱落条件（FBO）。在辐条-壳体连接处重复出现的局部接缝作为塑性变形和可能产生裂纹的最可能的位置，特别引起人们的兴趣。与先前的预测孤立的管状接头中的弹塑性力-位移响应的工作相似，这表明采用类似技术的可能性。因此，已经开发了基于辐条轴向载荷和弯矩的二维载荷空间中的互补能级曲线的辐条到外壳连接行为的预测程序。

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