A-21 ピエゾ素子を用いた遷音速翼列フラッターの能動制御に関する実験(空力V,一般講演)

概要

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Active suppression of transonic cascade flutter with piezoelectric device was experimentally studied based on the previous numerical results. The proposed control method in which the blade trailing edge was actively oscillated with piezoelectric device had been found to be effective for flutter suppression in the numerical study. In the present experiment, the effect of the control method was investigated in a linear cascade wind tunnel under a transonic flow condition. Unsteady aerodynamic force on the blades induced by the active oscillation was measured and superposed into the unsteady induced force causing flutter instability. The results showed substantial stabilizing effect on flutter instability in the case with appropriate phase of active oscillation.
公益社団法人日本ガスタービン学会の論文
2008-10-01