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Performance analysis of turbo-electric propulsion system with fuselage boundary layer ingestion

机译：机身边界层摄取涡轮电力推进系统的性能分析

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A propulsion system analysis of an aircraft concept featuring a fuselage tail cone integrated turbo electrically powered fan is presented. The aircraft has two underwing podded geared turbofan engines and an aft-fuselage mounted boundary layer ingesting fan. The fuselage fan is driven by an electric motor that is powered by power offtake from the main power plants under the wing. A long-range tube-and wing aircraft with a year 2050 entry into service is used as a reference. A coupled multidisciplinary method for system level assessment of the turbo-electric boundary-layer ingesting propulsion system is presented. A correlation-based method is used to predict fuselage drag and a series of optimizations are carried out for a range of fuselage fan diameters. The optimal level of ingested drag is 30%-57% of the total fuselage drag, resulting in a net reduction in mission fuel burn of 0.6%-3.6% depending on technology assumptions. Further analysis reveals that installation effects, mainly increased mass, offset some of the gains of boundary layer ingestion for the smallest fuselage fan sizes. For larger fan sizes, it is instead the losses in the electric machinery together with the lower efficiency of the fuselage fan, compared to the main engine fan, that compensate for the gains from boundary layer ingestion. However, the by far strongest effect for determining the optimal level of ingested drag is that it is very difficult to obtain a net benefit from ingesting the half of the total fuselage drag contained in the outer part of the boundary layer. The benefit is outweighed by losses in the electric transmission system, installation effects and efficiency deficits of having an aft-mounted fan instead of larger size under-wing main engines. This is true also under the assumption of radical technology such as superconducting electric machinery. It is concluded that the studied aircraft architecture, despite having a high theoretical potential, faces a large difficulty in beneficially ingesting the significant amount of the fuselage drag contained in the outer part of the boundary layer. This severely limits its potential to substantially reduce the fuel burn compared to a conventional twin-engine tube-and-wing aircraft in the year 2050 timeframe. (c) 2020 Published by Elsevier Masson SAS.
机译：提出了采用机身尾锥集成涡轮电动风扇的飞机概念的推进系统分析。该飞机有两个底翅齿轮涡轮机发动机和船尾安装的边界层摄取风扇。机身风扇由电动机驱动，电动机由机翼下的主要发电厂供电。使用2050年进入服务的远程管和翼飞机作为参考。提出了一种耦合的多学科方法，用于摄取推进系统的涡轮电界层的系统级评估。基于相关的方法用于预测机身拖动，并对一系列机身风扇直径进行一系列优化。由于技术假设，最佳摄入阻力水平为占总机身拖累的30％-57％，导致任务燃料燃烧的净减少0.6％-3.6％。进一步的分析表明，安装效果主要增加质量，抵消了为最小机身风扇尺寸摄取的边界层的一些收益。对于较大的风扇尺寸，与主发动机风扇相比，电机中的电机损耗与机身风扇的较低效率相比，这补偿了从边界层摄取的收益。然而，对确定最佳摄取阻力水平的最强烈效果是，非常难以从边界层的外部中包含的总机身拖拽中的一半获得净利。电动传输系统中的损失，安装效果和效率缺陷的损失超过了船尾风扇而不是翼型底部主发动机的损耗超过了益处。这也是如此，也是如此在超导电机的自由基技术之下。结论是，已经研究的飞机架构尽管具有高理论势，因此在有利地摄取有利地摄取附着在边界层的外部中包含的大量机身阻力的难度较大。与传统的双发动机管 - 翼飞机在2050次时间框架中，这严重限制了其基本上减少了燃料燃烧。 （c）2020由Elsevier Masson SA发表。

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