模拟转子叶片丢失后外传载荷影响特性研究

The aviation airworthiness law and related safety standards all set requirements for the safety design when aero engine blade off event happened，so it is necessary to clarify the load environment of key parts in the blade off event. In this paper，the Newmark-β method is used to solve the differential equation of transient motion of the load transfer system，and the relationship between vibration response and force load is obtained. A simulated rotor unbalance response test is designed，and the rotor response test after sudden unbalanced mass is carried out，and then the transmission law of shock load is obtained through the internal and external vibration response of the test piece. At the same time，in order to study the effects of damping on blade off of external load，a comparative test of vibration response with damping and without damping was carried out by controlling whether the damper of the test piece was supplied with oil. The results show that the shock load will be significantly attenuated after passing through the stator，the maximum transfer ratio of the tester in this paper is only 53%，and the load away from the rotor support is much lower than the load at the rotor support. At the same time，damping significantly reduces the external load at the moment of impact，but it has little effect on the steady-state load after the rotor is stabilized. Through the research of this paper，it is explained that the attenuation and damping effects of shock load should be considered when analyzing the safety of the aero engine in the blade off event. In addition，a reasonable damper layout will effectively reduce the shock load caused by the blade off event，which will help improving the impact resistance of the engine.