During the design of gas turbine aircraft engines, it is essential to analyze the vibration and damping characteristics of the rotationally cyclic structure experiencing traveling wave vibration. A finite element model of a single sector is established. The cyclic symmetry boundary conditions and Craig-Bampton reduction method are combined to construct a reduced order model. Based on the harmonic balance method, the structural forced responses under traveling wave excitation are calculated. By integrating the nonlinear complex vibrational pattern method, the proposed approach enables the calculation of the nonlinear vibrational pattern. A method based on the nonlinear vibrational pattern is proposed to calculate the resonant response of the blisk. A sensitivity analysis is conducted on the blisk with a ring damper, and a response surface model of the key design parameters is constructed. The results reveal two key findings: damping characteristics exhibit negligible sensitivity to traveling wave direction and increasing the ring damper cross-sectional dimension enhances peak damping ratios but may increase critical amplitudes. The actual blisk is modified to add a ring damper. A rotational excitation test is performed. The results show that the ring damper reduces the amplitude by approximately 80%. This method provides an effective tool for damping analysis and structural optimization of cyclic structures under traveling wave vibration.

In recent years, the hollow fan blades have been widely used to meet the demand for light weight and good performance of the aero-engine. However, the relationship between the hollow structure and the aeroelastic stability has not been studied yet in the open literature. In this paper, it has been investigated for an H-shaped hollow fan blade. Before studying the flutter behavior, the methods of parametric modeling and auto-generation of Finite Element Model (FEM) are presented. The influence of the feature parameters on the vibration frequency and mode shape (as the input of flutter calculation) of the first three modes are analyzed by the Orthogonal Experimental Design (OED) method. The results show that the parameters have a more remarkable impact on the first torsional mode and thus it is concerned in the flutter sensitivity analysis. Compared with the solid blade, the minimum aerodynamic damping of the hollow blade decreases, indicating that the hollow structure makes the aeroelastic stability worse. For the parameters describing the hollow section, the rib number N has the greatest influence on the minimum aerodynamic damping, followed by the wall thickness W₅. For the parameters in the height of hollow segment, the aerodynamic damping increases with the increase of parameters M₁ and M₂. This means that reducing the height of the hollow segment is helpful to improve the aeroelastic stability. Compared with the impact of parameters in hollow section, the variation of aerodynamic damping caused by the height of the hollow segment is small.