一种涡轮叶尖间隙主动控制系统的建模与仿真

摘要

为了提高现代航空发动机的性能,通过机械装置来控制(减小)涡轮叶尖间隙成为现在和未来的一个研究热点.在分析研究了航空发动机在不同工况下涡轮叶尖间隙的变化规律的基础上,提出了一种双闭环主动快速控制系统.进而,设计了一种可以控制非均匀叶尖间隙变化的作动装置,并对其进行了深入的数学建模分析.最后,分别通过PID和模糊PID两种控制器工作方式,对所设计的涡轮叶尖间隙主动快速控科系统的控制效果进行了仿真验证,结果表明,在起飞时段,PID控制曲线与模糊自适应PID控制曲线基本重合；但是在巡航、迅速减速、迅速加速、再次巡航时段,模糊自适应PID的控制效果要明显优于PID控制.%In order to improve the performance of modern aviation engine, reducing the turbine blade tip clearance by mechanical device becomes a hot research topic now and in the future. Based on the analysis of the re--tis esearchtion change nules of an engine's turbine blade tip clearance under different working conditions, an active -oqm fast colitiol sysfest with double closed loop is put forward, as well us, an actuator device which can control non--usnore umiform up clearance change of the engine is designed, and the thorough analysis of mathematical modeling is carried on. Finally, respectively through two working ways of the PID and fuzzy PID controller, the control effect of turbine tip clearance active fast control system is simulated. The results show (hat during the take-off time, PID control curve and the fuzzy adaptive PID cotrol curve are coindent basically: however, in the cruise, rapid slowdown, rapid acceleration, and the second cruise period of time, the control effect of fuzzy adaptive PID is significantly better than PID control.