航空发动机转子振动主动控制系统的综合设计

Synthetic Active Vibration Control for Rotor System of Aero-Engines

针对航空发动机转子振动控制的主要目的，将控制力分成三个分量，分别用于调整临界转速、抵消不平衡量、提供主动阻尼，并对各分量独立设计其最优控制律，然后对线性转子系统实施综合控制．仿真结果表明，控制力如此分工是合理可行的，综合控制的抑振效果十分显著。

The excessive vibration of aero-engine rotor often causes serious aeronautical faults.The main objectives of our synthetic active vibration control (SAVC) system of aero-engine rotor are: (1) to keep the critical rotating speeds of controlled rotor as much away from its working speed range as possible 1 (2) to make controlled rotor least sensitive to imbalance force in full working speed ranse; (3) to stabilize rapidly disturbed rotor.The synthetic control force is composed of three parts: (1) n1 is designed via pole assignment method to relocate the critical speeds of the system ; (2) u2 is designed to counteract the imbalance force of the rotor, including the sudden blade loss 1 (3) u3 is designed according to the LQR - SS[3] (SS - specific stability) of authors' previous work to provide enough active damping to reject disturbance and instability. Each controller ui(i=1 , 2, 3) isdesigned individually and then they are synthesized into total control input u in eq. (1).The model rotor of aero- engine in Ref. [2] is employed to demonstrate proposed synthetical Control scheme. The computation results are shown in Figs. 1 and 2, which show clearly that: (1) the proposed SAVC scheme can extend the steady working speed range ofthe rotor system by 200%; (2) the proposed SAVC scheme can practically completely suppress the imbalance responses within full working speed range.Much difficult experimental work remains to be done for applying the sythetic active vibration control scheme to actual aero-engine rotor system.