基于SQP的航空发动机加速规律优化方法

Acceleration control law optimization in aero engine based on SQP

提出了一种改善航空发动机加速性能的方法:采用SQP寻优方法对航空发动机进行加速过程的寻优控制仿真计算,获得以油/气压比为函数的优化加速燃油控制规律。选取工作包线内具有一定覆盖性的若干个状态点,进行加速过程寻优控制仿真。考虑到根据油/气压线开环进行加速控制易于导致涡轮后温度瞬态超调,提出了根据两类约束条件计算开环加速线,对所获得的两条优化的加速线进行融合,进而获得适用于全飞行包线范围内的加速燃油控制规律。仿真计算表明,所提出的加速燃油控制规律可以在兼顾涡轮后温度不超温和压气机喘振裕度的情况下,实现发动机加速时间最短的目标。

This paper proposes a new approach for improving aero engine performance. It optimized aero engine accelerations via SQP. Optimal acceleration control law,which is the function of fuel/pressure,was worked out. The simulation was carried out in numerous overlaid state points in engine work envelope. Control via the fuel/pressure curve may result in the turbine exit temperature overshoot momently. Computational acceleration curve based on two kinds of constraints consequently is presented. Two optimal curves were integrated ,and optimal acceleration control law was obtained. The simulation indicates that this approach can minimize accelerated time,considering both the turbine exit temperature and the stable margin of compressor.