基于冗余执行器的航空发动机推力快速响应控制方法研究  

Rapid thrust modulation control of aeroengines based on redundant actuators

作　　者：李睿超[1] 虞超 姚竞豪 郭迎清[1] 王兵[2] 王向阳[3] LI Ruichao;YU Chao;YAO Jinghao;GUO Yingqing;WANG Bing;WANG Xiangyang(School of Power and Energy,Northwestern Polytechnical University,Xi’an 710072,China;School of Aerospace Engineering,Tsinghua University,Beijing 100080,China;Institute for Aero Engine,Tsinghua University,Beijing 100080,China)

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072 [2]清华大学航天航空学院,北京100080 [3]清华大学航空发动机研究院,北京100080

出　　处：《推进技术》2024年第7期260-268,共9页Journal of Propulsion Technology

基　　金：国家科技重大专项。

摘　　要：面向飞/推一体化控制需求,开展涡扇发动机推力快速响应控制研究,提出了适用于推力最小相位系统的冗余控制方案。研究内容包括:(1)借鉴阀位控制思想,提出在传统燃油流量(Wf)回路基础上增设尾喷口喉道面积(A8)回路,通过挖掘冗余执行器变化速率潜力,提高推力响应速度,降低了对于燃油泵快速作动的需求,同时该方法可以使喷口在推力响应过程逐渐回中,系统具备持续的推力快速调节能力;(2)分析了A8调节推力的物理机理,指出容腔压力动力学主导的部件间流量匹配过程使得A8对推力具有直馈作用,是提高推力响应速度的有效途径。基于发动机部件级模型的评估结果表明,本文提出的方法在执行机构存在速率限制的情况下,实现了推力10 rad/s闭环带宽和A8回中的设计目标,方法可行、有效。在推力响应过程中,A8直馈作用对推力变化的贡献度最高时超过50%。随着对于推力控制模式和推力响应速度的日趋关注,应对容腔内的压力动态过程给予充分的重视。Facing the demand of flight/propulsion integrated control,this paper conducts research on rapid thrust modulation of turbofan engine,and puts forward a redundant control scheme suitable for thrust minimum phase system.The research content includes:(1)Using the idea of valve position control for reference,the noz-zle throat area(A8)loop is proposed based on the traditional fuel flow rate(Wf)loop.By utilizing the change rate potential of redundant actuators,the thrust response speed is improved,and the demand for fast operation of fuel pump is reduced.At the same time,this method can make the nozzle gradually return to its middle position in the process of thrust response,and the system has the ability of continuous thrust rapid adjustment.(2)The physical mechanism of A8 adjusting thrust is analyzed,and it is pointed out that the flow rate process between components dominated by chamber pressure dynamics makes A8 feed directly to thrust,which is an effective way to improve the speed of thrust response.The evaluation results based on the engine component-level model indicate that the method proposed in this paper,in the presence of actuator rate limits,achieves the design goals of thrust 10 rad/s closed-loop bandwidth and A8 return to its middle position.The method is feasible and effective.At the same time,in the process of thrust response,the contribution of A8 direct feedback to thrust change is more than 50%at the highest.With the increasing attention to thrust control mode and thrust response speed,full attention should be paid to the dynamic process of pressure in the chamber.

关 键 词：航空发动机 推力控制 推力快速响应 冗余执行器 最小相位系统 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]