High stress vibration fatigue test of several aeroengine blades were carried out on electric shaker and the test mechanism was studied. New test methods were put forward, which were blade maximal vibration stress monitoring using assisting points and fixed frequency excitation after resonance frequency. Open loop control technology of vibrating table was successfully applied to stabilize vibration stress and reliable fatigue data were obtained. The relation between the excitation of electric shaker and the vibration response of blade was discussed.
