摘要
航空发动机在运行过程中,由于其结构的复杂性和外部气流的不稳定性,不可避免地会产生大量的振动问题。针对航空发动机整机振动问题,首先根据航空发动机的实际结构并结合经验总结,建立了一种通用的转子‑支承‑机匣振动传递动力学模型,并从航空发动机内外机匣减振控制问题出发,利用一种新型的控制算法(几何设计法),在有限频域内来设计减振控制器,在传感器和执行机构受限的情况下,尝试对多个输出量(即航空发动机的内机匣和外机匣)进行减振控制,并与经典控制理论法比例、微分、积分(Proportional integral derivative,PID)设计的减振控制器进行减振效果对比,最后通过Matlab/Simulink搭建仿真模型并进行仿真验证。结果表明,几何设计法在有限频域内可以直观地获得最优控制器的存在性、唯一性、最优性,对于主控对象的减振控制最优可高达25 dB,相较于传统控制方法形成明显优势。
Due to the complexity of the structure and the instability of the external air flow,considerable problems inevitably occur during the operation of aero-engines.Aiming at the vibration problem of the whole aero-engine,a general dynamic model of rotor-support-casing vibration transmission is established according to the actual structure of the aero-engine and the summary of experience.Moreover,starting from the vibration control problem of the internal and external cases of the aero-engine,a novel control algorithm(geometric design method)is used to design the vibration reduction controller in the limited frequency domain.In the case of limited sensors and actuator,the controller is used to try to control the vibration of multiple outputs(i.e.,the inner and outer cases of the aero-engine),and compare the vibration reduction effect with the vibration reduction controller designed by proportional integral derivative(PID).Finally,the simulation model is built and verified by Matlab/Simulink.The results show that the geometric design method can intuitively obtain the existence,uniqueness and optimality of the optimal controller in the limited frequency domain,and the optimal vibration reduction control for the main control object can be as high as 25 dB.Compared with traditional control methods,the geometric design method has obvious advantages.
作者
安然
陈佳杰
杜潇
张海波
王继强
AN Ran;CHEN Jiajie;DU Xiao;ZHANG Haibo;WANG Jiqiang(College of Energy and Power Engineering,Nanjing University of Aeronautics&Astronautics,Nanjing 210016,China;Ningbo Institute of Materials Technology&Engineering,Chinese Academy of Sciences,Ningbo 315201,China)
出处
《南京航空航天大学学报》
CAS
CSCD
北大核心
2023年第4期622-633,共12页
Journal of Nanjing University of Aeronautics & Astronautics
关键词
航空发动机内外机匣
主动振动控制
有限频域
受限控制
几何设计法
internal and external cases of aero-engine
active vibration control
limited frequency domain
limited control
geometric design method
