Abstract
Rub-impact fault is a common problem in aircraft engines. To simulate the dynamic process and rubbing force, a finite element model of blade-coating rubbing was developed and verified experimentally through a rotor rig test. Considering the aero-engine's structural characteristics and material properties, a simulation model for rub-impact fault was developed. It considered the blade-casing-coating material model selection and parameter settings, constraints, contact, and load settings of the components, which was calculated using explicit-implicit integration scheme. A ‘0–2-1’ supported aero-engine rotor-blade-coating coupling system was also developed to study the rub-impact fault's influence on the system vibration response, combining the rubbing force obtained at different rotating speeds and invasion depths. Results show that the rotor vibration mainly concentrates on the fundamental frequency and its multiplications during blade-coating rubbing. Rotating speed significantly affects the vibration of the frequency multiplications. Moreover, the dynamic response of the rotor system varies considerably with the invasion depth.
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Lin, J., Wu, B., Lu, X., Xu, J., Zhang, J., Dai, H. (2024). Numerical Simulation of Aero-Engine Rotor-Blade-coating Coupling System with Rub-impact Fault and Its Dynamic Response. In: Chu, F., Qin, Z. (eds) Proceedings of the 11th IFToMM International Conference on Rotordynamics. IFToMM 2023. Mechanisms and Machine Science, vol 140. Springer, Cham. https://doi.org/10.1007/978-3-031-40459-7_4
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