| Citation: | LYU Qihang, CHEN Cheng, DENG Lijun, et al. Structure design and vibration reduction analysis of a certain type of un-derplatform damper[J]. Journal of Aerospace Power, 2026, 41（2）：20240122 doi: 10.13224/j.cnki.jasp.20240122
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To investigate the impact of blade platform damping devices on the dynamic response of vibration in a certain type of aero-engine gas turbine blades, a friction model was established based on the global-local unified slip model theory. By integrating the finite element analysis software ANSYS and harmonic response calculation procedures, simulation analysis was conducted on grouped three-tooth turbine blades. When the ratio of the normal pressure between the damper and the blade platform to the excitation force acting on the blade fell within an appropriate range, the simulated resonance amplitude of the second-order mode of the blade can be reduced to below 25% of the undamped state. Based on the simulation results, structural designs for two types of turbine blade platform dampers were completed. For high-frequency vibration modes of a certain turbine blade, a high-frequency vibration reduction test plan was designed, and a corresponding test system was constructed. High-order modal vibration reduction tests were carried out on grouped turbine blades, and the first-order resonance amplitude was reduced to 70.72% of the undamped state. By combining simulation results with experimental data, key parameters influencing the vibration reduction characteristics of turbine blades were identified, leading to the development of a comprehensive methodology for the structural design and experimental validation of turbine blade platform dampers under critical modal conditions.
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