A Vibration Suppression Method for the Multistage Rotor of an Aero-Engine Based on Assembly Optimization

Yue Chen,Jiwen Cui,Xun Sun

doi:10.3390/machines9090189

Yue Chen, Jiwen Cui + Show 1 more

Open Access

https://doi.org/10.3390/machines9090189

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Abstract

The assembly quality of the multistage rotor is an essential factor affecting its vibration level. The existing optimization methods for the assembly angles of the rotors at each stage can ensure the concentricity and unbalance meet the requirements, but it cannot directly ensure its vibration responses meet the indexes. Therefore, in this study, we first derived the excitation formulas of the geometric and mass eccentricities on the multistage rotor and introduced it into the dynamics model of the multistage rotor system. Then, the coordinate transfer model of the geometric and mass eccentricities errors, including assembly angles of the rotors at all stages, was established. Moreover, the mathematical relationship between the assembly angles of the rotors at all stages and the nodal vibration responses was established by combining the error transfer model with the dynamics model of the multistage rotor system. Furthermore, an optimization function was developed, which takes the assembly angles as the optimization variables and the maximum vibration velocity at the bearings as the optimization objective. Finally, a simplified four-stage high-pressure rotor system was assembled according to the optimal assembly angles calculated in the simulations. The experimental results showed that the maximum vibration velocity at the bearings under the optimal assembly was reduced by 69.6% and 45.5% compared with that under the worst assembly and default assembly. The assembly optimization method proposed in this study has a significant effect on the vibration suppression of the multistage rotor of an aero-engine.

Highlights

Vibration overrun is the main reason for the failure or damage to the rotating machinery such as aero-engine and gas turbines with multistage rotors [1,2]
Their assemscale according to the high-pressure rotor system of a real aero-engine and simplified as bly rabbets are tightly connected by twelve, twenty-four and twelve uniformly distributed a multistage rotor composed of four components: Rotor-1, Rotor-2, Rotor-3 and Rotor-4
We proposed a vibration suppression method for the multistage rotor of an aero-engine based on assembly optimization

Summary

Introduction

Vibration overrun is the main reason for the failure or damage to the rotating machinery such as aero-engine and gas turbines with multistage rotors [1,2]. Rotor misalignment and unbalance are the two most common factors causing the vibration on the multistage rotor system [3,4,5]. Rotor misalignment and unbalance often exist simultaneously, and the multistage rotor of an aero-engine often needs to be repeatedly balanced and disassembled to meet vibration indexes [6,7]. Optimization is to search the optimal assembly angles of the rotors at all stages to achieve the maximum vibration suppression of a multistage rotor without secondary repair. It can significantly improve the qualification rate of the one-time assembly and reduce the costs of manufacturing and test-run for an aero-engine

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Results

Discussion

Conclusion