Trade Studies for NASA N3-X Turboelectric Distributed Propulsion System Electrical Power System Architecture

Armstrong, Michael J.; Ross, Christine; Blackwelder, Mark; Rajashekara, Kaushik

doi:10.4271/2012-01-2163

Cited by 53 publications

(42 citation statements)

References 7 publications

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“…For the purposes of this study, the required power for rolling take-off is estimated to be 22.4 MW (30 000 HP) [17]. Hence under normal operation, the motors will each require circa 1.4MW of electrical power.…”

Section: Candidate Architecturesmentioning

confidence: 99%

Comparison of Candidate Architectures for Future Distributed Propulsion Aircraft

Jones

Norman

Galloway

et al. 2016

IEEE Trans. Appl. Supercond.

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This version is available at https://strathprints.strath.ac.uk/55472/ Strathprints is designed to allow users to access the research output of the University of Strathclyde. Unless otherwise explicitly stated on the manuscript, Copyright © and Moral Rights for the papers on this site are retained by the individual authors and/or other copyright owners. Please check the manuscript for details of any other licences that may have been applied. You may not engage in further distribution of the material for any profitmaking activities or any commercial gain. You may freely distribute both the url (https://strathprints.strath.ac.uk/) and the content of this paper for research or private study, educational, or not-for-profit purposes without prior permission or charge.Any correspondence concerning this service should be sent to the Strathprints administrator: strathprints@strath.ac.ukThe Strathprints institutional repository (https://strathprints.strath.ac.uk) is a digital archive of University of Strathclyde research outputs. It has been developed to disseminate open access research outputs, expose data about those outputs, and enable the management and persistent access to Strathclyde's intellectual output.This document is a pre-print which was accepted for publication in IEEE transactions on Applied Superconductivity on the 1 st of February 2016, and as such is subject to IEEE copyright.  Abstract-Turbine engine driven distributed electrical aircraft power systems (also referred to as Turboelectric Distributed Propulsion (TeDP)) are proposed for providing thrust for future aircraft with superconducting components operating at 77K in order for performance and emissions targets to be met. The proposal of such systems presents a radical change from current state-of-the-art aero-electrical power systems. Central to the development of such power systems are architecture design trades which must consider system functionality and performance, system robustness and fault ride-through capability, in addition to the balance between mass and efficiency. This paper presents a quantitative comparison of the three potential candidate architectures for TeDP electrical networks. This analysis provides the foundations for establishing the feasibility of these different architectures subject to design and operational constraints. The findings of this paper conclude that a purely AC synchronous network performs best in terms of mass and efficiency, but similar levels of functionality and controllability to an architecture with electrical decoupling via DC cannot readily be achieved. If power electronic converters with cryocoolers are found to be necessary for functionality and controllability purposes, then studies show that a significant increase in the efficiency of solid state switching components is necessary to achieve specified aircraft performance targets. Index Terms-Distributed electrical aircraft propulsion, superconducting power systems, turbo-electric distributed propulsion

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Section: Candidate Architecturesmentioning

confidence: 99%

Comparison of Candidate Architectures for Future Distributed Propulsion Aircraft

Jones

Norman

Galloway

et al. 2016

IEEE Trans. Appl. Supercond.

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“…The increase in system complexity provides significant challenges to develop an architecture with optimal performance in terms of weight and efficiency [3].…”

Section: ) Flexibilitymentioning

confidence: 99%

“…5. The power required by the loads on a single ring busbar was rated at 12.5 MW (half of the minimum 25 MW rolling take-off power available from a single engine) [3]. The total resistive load was taken to be 2 , as defined by the power rating of the loads and the system voltage.…”

Section: B Development Of System Modelmentioning

confidence: 99%

“…At a basic level, the fault management strategy underpinning all TeDP and conventional aircraft designs is mitigation against an engine-out failure scenario [3]. It is assumed that all fault management strategies for any chosen TeDP system will incorporate this essential capability and that the propulsors and other system components are sized accordingly [4].…”

Section: Introductionmentioning

confidence: 99%

“…However highly reliable, compact electrical networks require a wider view of fault management beyond engine failure [3]. Faults occurring downstream in the network also have to be considered since these too may contribute to a detrimental loss of thrust if the system does not respond appropriately.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Fault management strategies and architecture design for turboelectric distributed propulsion

Flynn

Jones

Norman

et al. 2016

2016 International Conference on Electrical Systems for Aircraft, Railway, Ship Propulsion and Road Vehicles &Amp; Internationa

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Abstract-The TeDP concept has been presented as a possible solution to reduce aircraft emissions despite the continuing trend for increased air traffic. However, much of the benefit of this concept hinges on the reliable transfer of electrical power from the generators to the electrical motor driven propulsors. Protection and fault management of the electrical transmission and distribution network is crucial to ensure flight safety and to maintain the integrity of the electrical components on board. Therefore a robust fault management strategy is required. With consideration of the aerospace-specific application, the fault management strategy must be efficient, of minimal weight and be capable of a quick response to off-nominal conditions. This paper investigates how the TeDP architecture designs are likely to be driven by the development of appropriate fault management strategies.

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Trade Studies for NASA N3-X Turboelectric Distributed Propulsion System Electrical Power System Architecture

Cited by 53 publications

References 7 publications

Comparison of Candidate Architectures for Future Distributed Propulsion Aircraft

Comparison of Candidate Architectures for Future Distributed Propulsion Aircraft

Fault management strategies and architecture design for turboelectric distributed propulsion

Current Status and Prospects of High-Speed Direct-Drive Power Generation Technology

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