# Study on Influence of Multi-Parameter Variation of Bladed Disk System on Vibration Characteristics
## 1 Introduction  
As the main components of the rotor system of aero-engines and other rotating machinery equipment, the bladed disk system has high requirements on its structure design and safety stability. Under the harsh conditions of high rotating speed, high temperature and high pressure, the bladed disk system is likely to scale and change in mass, causing blade damage and shedding due to high loading and centrifugal force. The change of blade mass and blade detachment will seriously affect the balance of the rotor system. The imbalance of the rotor system will cause serious accidents. In recent years, scholars have carried out theoretical, numerical simulation and experimental study on vibration and dynamic characteristics of the dissonant bladed disk system. [PERSON] et al. [1, 2] discussed on the numerical simulation analysis of dissonant bladed disk and obtained the results of localized modal analysis of a dissonant bladed disk. By comparing the experimental results, the results of modal analysis were very consistent with the experimental results. [PERSON] et al. [3] summarized various modeling principles based on finite element and methods for the disc-dissonance recognition, sensitivity analysis and forced response prediction. [PERSON] et al. [4] studied the forced response characteristics of the dissonant bladed disk using the reduced finite element model and found that the forced response of the bladed disk system with localized vibration mode would not necessarily increase significantly but might also decrease. From the statistical average, the forced response will increase, and the peak will appear with the increase of random dissonance. [PERSON] [5] studied the modal and forced vibration response of the dissonant bladed diskand projected it into the modal space of the harmonic bladed disk system. The results show that the proposed scheme can accurately describe the effect of dissonance on the structure vibration characteristics of the bladed disk system. [PERSON] [6] studied the localization problem of the inherent vibration of the bladed disk system by using the modeling method of centralized parameters on the bladed disk. The results show that the disk system is sensitive to random dissonance. [PERSON] et al. [7; 8; 9; 10] used the system modeling method of centralized parameters to obtain the maximum differential mode and maximum amplitude magnification coefficient of the blade stiffness dissonance of the corresponding coordinated system, indicating the local phenomenon of the system dissonance jump. In addition, based on the intelligent optimization method, the worst state mode localization method of dissonant disk structure is proposed. [PERSON] et al. [11] studied the rubbing of the mistuned bladed disk system with variable thickness blades, an elastically supported shaft-variable thickness blade-coupled finite element model was established. [PERSON] [12; 13; 14] established the finite element simulation model of the impeller, introduced the influence factors of wrong frequency, and analyzed the mode and probability response localization characteristics of the bladed disk system. The results show that the fault frequency can cause significant localization of vibration, and with the increase of dissonance, there will be a peak in the level of dynamic response and the degree of dispersion of the dissonant system. [PERSON] [15] studied the localization and periodic loss of system vibration caused by structural failure by establishing different models of the discordant bladed disk system. [PERSON] et al. [16] considered using active dissonance to reduce the sensitivity of the disc to random dissonance and chose a genetic algorithm to optimize the arrangement of two kinds of active dissonance blades A and B. [PERSON] and [PERSON] et al. [17; 18] presented a methodology for complex surface machining based on cutting forces prediction and described the implementation of a cutting force prediction model.