Integrated Control Design for a Partially Turboelectric Aircraft Propulsion System

IF 1.4 4区 工程技术 Q3 ENGINEERING, MECHANICAL Journal of Engineering for Gas Turbines and Power-transactions of The Asme Pub Date : 2023-10-11 DOI:10.1115/1.4063715
Donald L Simon, Santino J. Bianco, Marcus Horning
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Abstract

Abstract Electrified Aircraft Propulsion (EAP) holds great potential for reducing aviation emissions and fuel burn. A variety of EAP architectures have been proposed including partially-turboelectric configurations that combine turbofan engines with motor-driven propulsors. Such architectures exhibit coupling between subsystems and thus require an integrated control solution. This paper presents an integrated control design strategy for a commercial single-aisle partially-turboelectric aircraft concept consisting of two wing-mounted turbofan engines and an electric motor driven tailfan propulsor. The turbofans serve the dual purpose of generating thrust and supplying mechanical offtake power used to generate electricity for the tailfan motor. The propulsion control system is tasked with coordinating turbofan and tailfan operation under both steady-state and transient scenarios. The paper introduces a linear state-space representation of the architecture reflecting the coupling between the turbofan and tailfan subsystems along with loop transfer functions reflecting open- and closed-loop system dynamics. Also discussed is an applied strategy for scheduling the tailfan setpoint command based on the average sensed fan speed of the two turbofans. This approach ensures synchronized operation of the turbofan and tailfan subsystems while also allowing the turbofan fuel control design to be simplified. Performance of the integrated control design is assessed through a real-time hardware-in-the-loop test. Results from this facility test are presented to illustrate the efficacy of the applied integrated control design approach under steady-state and transient scenarios.
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部分涡轮动力飞机推进系统集成控制设计
电气化飞机推进(EAP)在减少航空排放和燃料消耗方面具有巨大的潜力。目前已经提出了多种EAP架构,包括将涡扇发动机与电机驱动推进器相结合的部分涡轮电动配置。这样的体系结构展示了子系统之间的耦合,因此需要一个集成的控制解决方案。本文提出了一种由两台安装在机翼上的涡扇发动机和一台电动机驱动的尾扇推进器组成的商用单通道部分涡扇电动飞机的综合控制设计策略。涡轮风扇具有双重作用,即产生推力,并提供用于为尾扇电机发电的机械附加动力。推进控制系统的任务是在稳态和瞬态情况下协调涡扇和尾扇的运行。本文介绍了反映涡扇和尾扇子系统之间耦合的体系结构的线性状态空间表示,以及反映开环和闭环系统动力学的回路传递函数。还讨论了一种基于两台涡扇的平均感应转速来调度尾扇设定值命令的应用策略。这种方法确保了涡扇和尾扇子系统的同步运行,同时也简化了涡扇燃油控制设计。通过实时硬件在环测试对集成控制设计的性能进行了评估。该设施试验的结果说明了应用综合控制设计方法在稳态和暂态情况下的有效性。
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来源期刊
CiteScore
3.80
自引率
20.00%
发文量
292
审稿时长
2.0 months
期刊介绍: The ASME Journal of Engineering for Gas Turbines and Power publishes archival-quality papers in the areas of gas and steam turbine technology, nuclear engineering, internal combustion engines, and fossil power generation. It covers a broad spectrum of practical topics of interest to industry. Subject areas covered include: thermodynamics; fluid mechanics; heat transfer; and modeling; propulsion and power generation components and systems; combustion, fuels, and emissions; nuclear reactor systems and components; thermal hydraulics; heat exchangers; nuclear fuel technology and waste management; I. C. engines for marine, rail, and power generation; steam and hydro power generation; advanced cycles for fossil energy generation; pollution control and environmental effects.
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