Dynamics of gas-turbine blades are particularly aero-elastic coupling sensitive. These aerodynamic limits can be
pushed away by adding extra damping to the structure in order to reach even better compressor performance.
However nowadays design and manufacturing techniques in aero-mechanics are achieving their maximum of
As in many fields active control would solve easily this kind of instability. But the diffculty remains in the
needed energy supply for actuators whereas these components are aimed to be bonded on rotating structures.
The capacity of different auto-supplied devices using shunted piezoelectric circuits had been studied here to
prevent turbomachine bladed from fluttering.
Before realizing the study on complex turbomachine geometries, the presented technique uses a numerical
development thanks to a 1D Euler-Bernoulli beam model combining both mechanical and electrical coupling
parameters. A second development thanks to a 3D model had been made using a commercial tool, Comsol
software. These approximate models are used to optimize electrically the shunted piezoelectric element and its
localization. The results, verified experimentally, let suppose that vibrations can be reduced signiffcantly when
shunted piezoelectric circuits are mounted on a real structure.