Vibrational model for a gas turbine combustion chamber gotten from experimental tests

This paper describes a procedure to get a vibrational model of a combustion chamber from a gas turbine, with the purpose to set the basis of a future acoustic phenomenon analysis. The combustion chamber model is grounded in a sub-damped modal model in which its freedom degrees are according with its flexible modal modes and their corresponded natural frequencies which were gotten from impact tests performed along the axial axis of the combustion chamber.