Anatomy of a 20 MW Electrified Aircraft: Metrics and Technology Drivers

P. Kshirsagar, J. Ewanchuk, B. V. van Hassel, Russell D. Taylor, S. Dwari, J. Rheaume, C. Lents
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引用次数: 5

Abstract

Development of electric, hybrid and turboelectric propulsion technologies for electrified aircraft propulsion system is essential for improving fuel consumption, reducing emissions and noise pollution, lowering maintenance costs and improving reliability of the air transportation systems. The future needs and key benefits of aircraft electrification has made it a highly persuaded common technology trend across the aerospace industry ranging from very large airplanes to small aircrafts, all alike. For very high power (20MW) propulsion system, with the inadequacies of current and near future state-of-the art of electric energy storage technologies, all electric aircraft solution faces enormous technology gaps that needs to be bridged. Advanced turbo-electric technology offers potential solutions towards successful realization of the benefits of electrification of aircrafts. However, this represent a grand challenge in many fronts to realize electric drivetrain (EDT) designs that would significantly improve fuel burn reduction, design flexibility, and operational improvements in next generation of aircrafts. This work focuses on the underlying technological elements to enable such high power turbo-electric aircraft. A preliminary study is carried out to find that to achieve the key benefits of electrifications, the ETD system efficiency has to be > 93% and the specific power density of the system is required to be > 7.5 kW/kg. Furthermore, it is found that that to achieve such system level performances, the EDT components is required to be ≥ 99% and with specific power densities > 40 kW/kg to achieve the 7.5 kW/kg target. These necessitates orders of magnitude of improvements at all technological fronts and requires radical improvement in design and integration methodologies. Major technologies and design trades for various components and system architectures are presented to provide guidelines and framework to address this grand challenge. Key results are provided to support the design study.
剖析一架20兆瓦的电气化飞机:指标和技术驱动
电气化飞机推进系统的电力、混合动力和涡轮电力推进技术的发展对于提高燃油消耗、减少排放和噪音污染、降低维护成本和提高航空运输系统的可靠性至关重要。飞机电气化的未来需求和主要优势使其成为整个航空航天业(从超大型飞机到小型飞机)的一种非常有说服力的共同技术趋势。对于大功率(20MW)推进系统,由于当前和近期储能技术的不足,所有电动飞机解决方案都面临着巨大的技术差距,需要弥合。先进的涡轮电力技术为成功实现飞机电气化的好处提供了潜在的解决方案。然而,实现电动传动系统(EDT)设计在许多方面都是一个巨大的挑战,这将显著提高下一代飞机的燃油消耗减少、设计灵活性和操作改进。这项工作的重点是实现这种大功率涡轮电动飞机的潜在技术要素。初步研究发现,要实现电气化的关键效益,ETD系统效率必须> 93%,系统的比功率密度必须> 7.5 kW/kg。此外,研究发现,要达到这样的系统级性能,EDT组件的比例必须≥99%,比功率密度> 40 kW/kg,才能达到7.5 kW/kg的目标。这需要在所有技术前沿进行数量级的改进,并需要在设计和集成方法方面进行根本性的改进。介绍了各种组件和系统架构的主要技术和设计交易,以提供应对这一重大挑战的指导方针和框架。提供了支持设计研究的关键结果。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
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