航空发动机加力燃油流量寻优控制方法

Afterburning Fuel Flow Optimal Control

为了实现带加力航空涡扇发动机最大推力寻优,作为途径之一,提出了一种新的加力燃油流量寻优控制方法。在常规开环的加力燃油流量控制计划的基础上,叠加一个闭环的寻优修正,以余气系数、加力燃烧室出口温度、喷口面积等参数为约束条件,并给出了不可测约束参数的解析计算方法以及解析余度校验方法。以某航空发动机动态模型为例进行了寻优控制方法的仿真验证,结果表明,采用新的加力燃油寻优控制方法,在包线范围内平均可以将发动机最大推力提高6%左右,并具备较好的寻优控制安全性。

A new approach about afterburning fuel flow optimal control was proposed for a mode of maximized aero engine thrust. A close loop amendatory fuel flow was added based on original open loop afterbuming fuel flow control law. The constraints include excess air coefficient, afterburning exit temperature, nozzle area, etc. The calculation method of unmeasurable constraint parameters and test method were indicated. The optimization was simulated with an engine dynamic model. The results indicated that the new approach can increase thrust by 6% in average and the optimization security is good.