双转子转速协同规划的涡扇发动机加减速控制计划研究

Acceleration and deceleration control schedule of turbofan engine based on cooperative scheduling of dual rotor speeds

关键词:  涡扇发动机  分阶段控制计划  加速进程划分  动态稳定法  超调临界点

Key words:  Turbofan engine  Phased control schedule  Acceleration process division  Fixed dynamic method  Overshoot critical point

摘要:

当前涡扇发动机加减速控制计划，不能规划双轴加速进程，导致加速末期推力波动。本文提出了分阶段的加速度控制计划，按边界约束划分加速进程，基于动态稳定法设计初始加速度计划，通过寻找系统参数的超调临界点，协同修正初始加速度计划，满足边界约束的同时保证双转子加速时间相同。在仿真验证环节，与基于定状态法的控制计划比较，本文方法可避免燃油振荡现象，推力超调量降低2.43%，推力稳定时间缩短1.045 s；与等转速增量的加速度控制计划比较，进一步改进了本文方法，推力响应时间缩短0.24 s，控制计划设计耗时为7.578 1 s。综上，本文方法缩短了推力超调量和推力稳定时间，有望应用于发动机控制计划在线计算。

Abstract:

Current turbofan engine’s acceleration and deceleration control schedule cannot coordinate two shafts’ acceleration process， resulting in thrust fluctuation at the end of acceleration. Phased control schedule is proposed， which divides acceleration process by boundary constraints， uses fixed dynamic method to design initial acceleration schedule， and modifies it by finding the parameters’ overshoot critical point. The schedule satisfies boundary constraints and ensures two rotors’ same acceleration duration. In simulation， compared with fix state control schedule， the method in this paper avoids fuel oscillation and reduces thrust overshoot by 2.43% and stabilization time by 1.045 s. Compared with equal speed incremental acceleration schedule， the method in this paper is modified and thrust response time is reduced by 0.24 s， acceleration schedule calculation time is reduced by 7.578 1 s. In summary， the method in this paper reduces thrust overshoot and stabilization time and can be applied to control schedule online calculation.