Dynamic vibration analysis of high-speed rotating blades

In order to address the issue of vibration in rotating blade systems, a nonlinear dynamic mathematical model was introduced. This model describes the system's physical characteristics. A theoretical analysis was conducted to examine the nonlinear dynamic behavior of rotating blades under the influence of aerodynamic and viscoelastic damping mechanisms. This analysis was conducted without considering the double gyroscopic effect. The dynamic equations underwent discretization by Galerkin truncation. The present study builds upon the foundation of pre-twisted blade models by incorporating thin plates as a component of system modeling. Based on Hamilton's principle, the dynamic control equations governing viscoelastic plates and their boundary conditions were derived. This study provides a theoretical foundation for vibration control of rotating blades and offers robust technical support for performance optimization and safety enhancement in aircraft engines. This support is derived from in-depth research into the nonlinear dynamics of rotating blades.