[en] A numerical methodology is described to design a frictional damper for blade structure
within aircraft engine. A finite element beam-platform model is used for preliminary design
stage. The frictional damper is designed based on two parameters, contact angle and vertical
position of the platform. Nonlinear modal analysis is used to investigate the nonlinear dynamic behaviour and damping performance.
Disciplines :
Mechanical engineering
Author, co-author :
Sun, Y
Yuan, J
Pesaresi, L
Denimal, E
Salles, Loïc ; Université de Liège - ULiège > Aérospatiale et Mécanique (A&M) ; Université de Liège - ULiège > Département d'aérospatiale et mécanique > Vibration of Turbomachines ; Imperial College London > Mechanical Engineering > Vibration University Technology Center
Language :
English
Title :
Using Complex Nonlinear Normal Mode to Design a Frictional Damper for Bladed Disk
Publication date :
2019
Event name :
7th International Conference on Nonlinear Vibrations, Localization and Energy Transfer
