“An Analysis Of Effect Of Variation In Reynolds Number On Aerodynamic Damping Of Aerofoil Blade With Feasibility Of Active Damping Method”

Aerodynamic damping decreases with low Reynolds, while it increases higher value. With numerical simulation and experimental techniques are applied to analyse how the Reynolds number affects a vibrating air foil blade. Low Reynolds range is applied to pitching air foil blade. Steady and unsteady laminar separation takes place simultaneous over the air foil blades which indicates that, unsteady laminar separation takes place during the transition process following the separated boundary layers separation in an unsteady flow. In the vibrating condition, the rise in Reynolds number results in reattachment and uneven laminar separation. For Re = 4×105 at lower Reynolds number pressure on the surface is substantially maximum at the pressure differential out of both aero foil surfaces is minimum as the Reynolds number is increased. The pressure distribution is comparable for Re= 2×106 and Re = 4× 106. Therefore, it is also studied that using Finite Element Simulation method, number of active and passive techniques have been used to analyses the flow over different aerofoil blades which equipped with piezoelectric actuator. It constitutes relationship in ANSYS and places the piezoelectric actuator in the optimise location. Piezoelectric actuator is attached to the front side of the blade and it is expected that both will adhere perfectly. The attempt is made to analyse for natural frequency and mode shape determination. Active control system provides proactive rather than merely damping response.