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Nonlinear effects of bolted flange connections in aeroengine casing assemblies
Mechanical Systems and Signal Processing ( IF 7.9 ) Pub Date : 2021-09-20 , DOI: 10.1016/j.ymssp.2021.108433
Seyed-Ehsan Mir-Haidari 1 , Kamran Behdinan 1
Affiliation  

Aeroengine manufacturers face fundamental limitations when correlating experimental dynamic analysis with finite element method models. The source of inconsistency between model predictions and experimental test data can be attributed to nonlinear behaviour at the bolted flange interface. The two main sources of nonlinearities in aeroengine casing assemblies are damping dissipation and the nonlinear effects of boundary conditions. In this research, a novel and robust analytical formulation is proposed for implementation in FE analysis that accurately captures and represents the nonlinear dynamic characteristics of bolted flange connections. The proposed nonlinear analytical lump model has demonstrated significant accuracy and precision in capturing the nonlinear dynamic characteristics of bolted flange connections with spigots under various loading conditions. The proposed model clearly represents and characterizes the nonlinear phenomena of peak amplitude damping and frequency shift. It is also computationally efficient, making the model feasible for implementation when performing nonlinear analyses of large structural assemblies such as full aeroengine models. Moreover, the proposed analytical lump model is universal, permitting its implementation in various structures with different material properties and geometries. The validity and accuracy of the proposed model has been verified using nonlinear experimental test data for an aeroengine casing assembly.



中文翻译:

航空发动机壳体组件中螺栓法兰连接的非线性效应

在将实验动态分析与有限元方法模型相关联时,航空发动机制造商面临着基本限制。模型预测和实验测试数据之间不一致的根源可归因于螺栓法兰接口处的非线性行为。航空发动机壳体组件非线性的两个主要来源是阻尼耗散和边界条件的非线性效应。在这项研究中,提出了一种新颖且稳健的分析公式,用于在有限元分析中实施,该公式可准确捕获和表示螺栓法兰连接的非线性动态特性。所提出的非线性分析块模型在捕捉各种载荷条件下带套管的螺栓法兰连接的非线性动态特性方面表现出显着的准确性和精度。所提出的模型清楚地表示和表征峰值振幅阻尼和频移的非线性现象。它的计算效率也很高,使模型在执行大型结构组件(如完整的航空发动机模型)的非线性分析时可行。此外,所提出的分析块模型是通用的,允许其在具有不同材料特性和几何形状的各种结构中实施。所提出模型的有效性和准确性已经通过航空发动机壳体组件的非线性实验测试数据进行了验证。所提出的模型清楚地表示和表征峰值振幅阻尼和频移的非线性现象。它的计算效率也很高,使模型在执行大型结构组件(如完整的航空发动机模型)的非线性分析时可行。此外,所提出的分析块模型是通用的,允许其在具有不同材料特性和几何形状的各种结构中实施。所提出模型的有效性和准确性已经通过航空发动机壳体组件的非线性实验测试数据进行了验证。所提出的模型清楚地表示和表征峰值振幅阻尼和频移的非线性现象。它的计算效率也很高,使模型在执行大型结构组件(如完整的航空发动机模型)的非线性分析时可行。此外,所提出的分析块模型是通用的,允许其在具有不同材料特性和几何形状的各种结构中实施。所提出模型的有效性和准确性已经通过航空发动机壳体组件的非线性实验测试数据进行了验证。在对大型结构组件(如全航空发动机模型)进行非线性分析时,使该模型可行。此外,所提出的分析块模型是通用的,允许其在具有不同材料特性和几何形状的各种结构中实施。所提出模型的有效性和准确性已经通过航空发动机壳体组件的非线性实验测试数据进行了验证。在对大型结构组件(如全航空发动机模型)进行非线性分析时,使该模型可行。此外,所提出的分析块模型是通用的,允许其在具有不同材料特性和几何形状的各种结构中实施。所提出模型的有效性和准确性已经通过航空发动机壳体组件的非线性实验测试数据进行了验证。

更新日期:2021-09-20
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