Abstract
Tabu genetic cat swarm optimization algorithm is proposed for optimization arrangement on mistuned blades. Furthermore, it is improved to be an innovative parallel algorithm based on Compute Unified Device Architecture (CUDA), whose performance is analyzed both in continuous and discrete solution space. The lumped parameter model and finite element model of the bladed-disk system are established for dynamics analysis and optimization verification. The complete mistuned parameter identification method and the improved mixed-interface prestressed substructure modal synthesis method are two other highlights. The results indicate that the algorithm in this paper has the advantages of low cost and high efficiency. The vibration localization and amplitude of the mistuned bladed-disk system are both reduced significantly. The optimization analysis method is proved to be applicable to the mistuned bladed-disk system of the aeroengine in engineering practice.
Highlights
IntroductionAeroengine is known as “the crown of mechanical industry.” e vibration failure accounts for over 60% of the total
More than 70% of these are caused by blades. e unbalanced vibration by reason of uneven vibration energy distribution is one of the main causes [1,2,3,4,5,6,7,8,9,10]. e bladed-disk system of aeroengine is a circular symmetric structure. e physical properties and geometric conditions of each blade are identical. e modes are uniformly distributed around the circle. ere is a small amount of difference in each sector because of the manufacturing error, material property, uneven wear, and so on. is small difference is called mistuning in structural dynamics
It is improved to be an innovative parallel algorithm based on Compute Unified Device Architecture (CUDA). e lumped parameter model and finite element model of the bladed-disk system are established for dynamics analysis. e complete mistuned parameter identification method and the improved mixed-interface prestressed substructure modal synthesis method are proposed for optimization verification
Summary
Aeroengine is known as “the crown of mechanical industry.” e vibration failure accounts for over 60% of the total. Petrov et al [11] and Petrov and Ewins [12] presented a new method for dynamic analysis of mistuned bladed disks based on the exact relationship between tuned and mistuned systems and solved the optimization problem of determining the worst mistuning patterns. Salhi et al [18] presented two methods for the identification of the vibration characteristics of rotating engine blades from time response measurements. Ganine et al [19] reviewed the static mode compensation method to predict geometrical mistuning effects on the response of bladed disks and analyzed its limitations. E complete mistuned parameter identification method and the improved mixed-interface prestressed substructure modal synthesis method are proposed for optimization verification It is of great significance for improving the reliability, reducing the failure rate, and increasing the interchangeability of blades in the aeroengine
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