A mode shape sensitivity-based method for damage detection of structures with closely-spaced eigenvalues

Measurement ◽  
2022 ◽  
pp. 110644
Author(s):  
Sahar Hassani ◽  
Mohsen Mousavi ◽  
Amir H. Gandomi
2015 ◽  
Vol 334 ◽  
pp. 377-387 ◽  
Author(s):  
Rune Brincker ◽  
Manuel Lopez-Aenlle

2021 ◽  
Vol 11 (10) ◽  
pp. 4589
Author(s):  
Ivan Duvnjak ◽  
Domagoj Damjanović ◽  
Marko Bartolac ◽  
Ana Skender

The main principle of vibration-based damage detection in structures is to interpret the changes in dynamic properties of the structure as indicators of damage. In this study, the mode shape damage index (MSDI) method was used to identify discrete damages in plate-like structures. This damage index is based on the difference between modified modal displacements in the undamaged and damaged state of the structure. In order to assess the advantages and limitations of the proposed algorithm, we performed experimental modal analysis on a reinforced concrete (RC) plate under 10 different damage cases. The MSDI values were calculated through considering single and/or multiple damage locations, different levels of damage, and boundary conditions. The experimental results confirmed that the MSDI method can be used to detect the existence of damage, identify single and/or multiple damage locations, and estimate damage severity in the case of single discrete damage.


2012 ◽  
Vol 331 (2) ◽  
pp. 291-307 ◽  
Author(s):  
Yao Zhang ◽  
Longqi Wang ◽  
Zhihai Xiang
Keyword(s):  

Author(s):  
Jing Li ◽  
Suryarghya Chakrabarti ◽  
Wei-Min Ren

Abstract Turbomachinery blade mode shapes are routinely predicted by finite element method (FEM) programs and are then used in unsteady computational fluid dynamic (CFD) analyses to predict the aerodynamic damping. This flutter stability assessment process is critical for the last-stage blades (LSBs) of modern heavy-duty gas turbines (HDGTs) which can be particularly susceptible to flutter. Evidences suggest that actual mode shapes may deviate from the FEM predictions due to changes in the FEM boundary or loading conditions, effects of the nonlinear friction contacts, and blade-to-blade variations (mistuning), among others. This uncertainty in the mode shape is accompanied by a general lack of knowledge on the sensitivity of the aerodynamic damping to a small change in mode shape. This paper presents a method to perturb a mode shape and estimate the corresponding change in aerodynamic damping in a framework enabled by linear theories and a rigid-body, quasi-3D treatment of mode shapes. This method is of low computational cost and is suitable for use in the preliminary design cycle. The numerical validation and applications of the method are demonstrated on two LSB blades. Results suggest that the mode shape sensitivity can be substantial and may even exceed the change in aerodynamic damping of a frictionally damped system when subjected to various levels of excitation.


2015 ◽  
Vol 347 ◽  
pp. 266-278 ◽  
Author(s):  
Wei Xu ◽  
Maosen Cao ◽  
Wiesław Ostachowicz ◽  
Maciej Radzieński ◽  
Ning Xia

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