Numerical investigation of forced response in the bladed disks with frictional damping in blade root section

The stress produced by vibration is a common and well investigated problem in the word of aviation. The stress caused by vibration can drastically reduce the life of a turbine engine and one of the main affected part of the engine are the blades. Design a last generation of gas turbine engine focusing on its reliability is a complicated task that can present a lot of problems. The blade has to be connected to the disk and before provide this assembly the dynamic behaviour must be predicted using different calculation methods available. The Finite Element Method (FEM) is one of the numerical methods that can solve the engineer calculation and and more precise than the analytical one. The dumping evolved in contact surfaces between the root blade and the disk perform a fundamental rule in the dynamic analysis of a bladed disk and predict how it change the dynamic behaviour of the system is one of the task requested during the design of the disk assembly. A numerical model based on the contact mechanics principles is performed and using a finite element modelling software is possible to use that theory and evaluate a result. This procedure allow to quantify the dumping generated at the contact of the root blade and the disk for different friction coefficients.