Active Control of Cascade Flutter with Piezo Electric Device in Transonic Flow
Details
A flow-structure coupled numerical method was developed to study the possibility of active control of cascade flutter. With the intention of applying piezo electric device, numerical analyses were performed under transonic flow conditions. In the cascade model adopted for this study, the unsteady aerodynamic force induced by passage shock wave was dominant for blade vibration stability. To control the passage shock movement, the method in which the trailing edge of blade was actively vibrated was sought. The method was revealed to change the unsteady aerodynamic force acted on the blade from exciting force to damping force if the phase of trailing edge oscillation was properly selected. To confirm the possibility of active control of cascade flutter, on/off control method with trailing edge oscillation was numerically simulated by flow-structure coupled method. From the results, it was revealed that increase in blade amplitude was suppressed by this control.
