Abstract
Aeroengine is a complex mechanical equipment, and it works at high temperature, pressure, rotational-speed, and severe loads. One of the core problems is that the vibration and mistuning of bladed disk lead to failure and affect the safety and reliability of aeroengine. Previously, one sector taken as the research object is not suitable; the integrally mistuned bladed disk (blisk) is taken as the research object is very necessary; however, the computational efficiency of mistuned blisk is very low. Therefore, a reduced-order model approach, i.e., an improved dynamic substructure finite element model-based state-space technique (IDSFEM-SST), is proposed to investigate the mistuned blisk. Firstly, the reduced-order substructure finite element model is established by this method, and then, the modal frequencies and modal strain energy amplitudes are investigated. Secondly, the maximum displacement responses are analyzed. Finally, the computational efficiency and accuracy of mistuned blisk via IDSFEM-SST is compared with that of the classical dynamic substructure finite element model and the high-fidelity finite element model to verify the effectiveness of this approach. This study has significance to the dynamic research and engineering practices for complex mechanical structures.
Highlights
The bladed disk is a complex rotational mechanical structure, which is one of the key functional transformation components of aeroengine
It will take a lot of time, and the requirement of the computer configuration is very high if the high-fidelity finite element model method (HFFEMM) is directly adopted
In order to improve the computational efficiency in the condition of ensuring the computational accuracy, a methodology termed as improved dynamic substructure finite element model method based on state-space technique (IDSFEM-SST) is proposed to analyze the vibration characteristics of the mistuned blisk for aeroengine, which is of great significance to theoretical research and engineering application
Summary
The bladed disk is a complex rotational mechanical structure, which is one of the key functional transformation components of aeroengine. The single blade or sector is regarded as the research object using Campbell diagram to avoid resonance is not suitable; the mistuned blisk is regarded as the research object is necessary to study its vibration response characteristics It will take a lot of time, and the requirement of the computer configuration is very high if the high-fidelity finite element model method (HFFEMM) is directly adopted. In order to improve the computational efficiency in the condition of ensuring the computational accuracy, a methodology termed as improved dynamic substructure finite element model method based on state-space technique (IDSFEM-SST) is proposed to analyze the vibration characteristics of the mistuned blisk for aeroengine, which is of great significance to theoretical research and engineering application
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