Blade oscillation mechanism for aerodynamic damping measurements at high reduced frequencies

Accurate prediction of aerodynamic damping is essential for flutter and forced response analysis turbomachinery components. Reaching a high level confidence in numerical simulations requires that the models have been validated against experiments. Even though number test cases established over past decades, there still lack suitable detailed data can be used validation purposes particular when it comes to aero at reduced frequencies which more relevant context analysis. A new transonic cascade rig, currently undergoing commissioning KTH, has designed with goal provide blade surface unsteady pressure compressor blades profiles oscillating frequencies. The paper provides an overview actuation system employed rig presents result series bench tests characterizing vibration amplitudes achieved this system.