An Experimental Investigation of Aerofoil Blade Naca-63415 Vibration Suppression by Using PZT Actuator Under Dynamic Condition in Absence of Aerodynamic Damping

Abstract

An experimental study along with numerical simulation to be able to analyse Reynolds numbers impact on vibrating air foil blade. Aerofoil blade vibrates at lower Reynolds number of flows i.e., Re = 4 × 106 and above this range the damping effect is cause by Aerodynamic damping. To counterbalance the vibration below certain range of Re = 2 ×106 to Re=4 × 106 of flow, so an aerofoil blade that function as cantilever beam with and without PZT patches is subject of an experimental study. Free vibration of aerofoil blade with 45°, 60° & 90° fiber orientation is conducted by varying the initial voltage supply of surface attached PZT Actuator. The actuator (Lead Zirconium Titanate) is used to mitigate the vibration levels to determine damping factor along with blade settling time. As PZT actuator added to blade surface, stiffness and mass of an experimental material increases which is leading to alterations in its natural frequency and the optimization of the patch position on the blades surface. GFRP material structure gives efficient vibration suppression smart with advanced, reliable composite system and PZT actuator acts as a smart damping device, in extended application to turboprop engines. This will be improving reliability and reduce fatigue failures in blades.