Turbo-electric distributed propulsion – opportunities, benefits and challenges

Nalianda, Devaiah; Singh, Riti

doi:10.1108/aeat-03-2014-0035

Cited by 23 publications

(12 citation statements)

References 15 publications

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“…A HEPS can be defined as a propulsion system that combines a conventional propulsion system with an electrical propulsion system in order to achieve better overall performance and/or lower emissions. 19 This paper focuses on an electrically assisted propulsion system (EAPS), a variation of HEPS in which the electrical system is used as a secondary system that would be running in parallel and would assist the existing propulsion system in certain flight phases to increase the overall efficiency. The EAPS system is considered in this paper because the energy-to-weight ratio of electrical batteries is significantly lower than those of the conventional propulsion system and hydrocarbon fuel.…”

Section: Electrically Assisted Propulsion Systemmentioning

confidence: 99%

Performance analysis of an electrically assisted propulsion system for a short-range civil aircraft

Ang

Rao

Kanakis³

et al. 2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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With civil aviation growing at around 4.7% per annum, the environmental footprint of aviation is increasing. Moreover, the use of kerosene as a fuel accelerates the depletion of non-renewable fossil fuels and increases global warming. Hence, the aviation industry has to come up with new technologies to reduce its environmental impact and make aviation more sustainable. An electrically assisted propulsion system can combine the benefits of an electrical power source with a conventional turbofan engine. However, the additional electrical system increases the weight of the aircraft and complexity of the power management system. The objective of this research is to analyze the effect of an assistive electrical system on the performance of a turbofan engine for an A320 class aircraft on a short-range mission. The developed simulation model consists of an aircraft performance model combined with a propulsion model. The power management strategy is integrated within the simulation model. With the proposed propulsion system and power management strategy, the electrically assisted propulsion system would be able to reduce fuel burn, total energy consumption, and emissions for short-range missions of around 1000 km.

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Section: Electrically Assisted Propulsion Systemmentioning

confidence: 99%

Performance analysis of an electrically assisted propulsion system for a short-range civil aircraft

Ang

Rao

Kanakis³

et al. 2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…6) The bypass ratios optimal for the turbine inlet temperatures higher than 1800 K correspond to the turbopropfan engine (considering the traditional schemes of gas turbine engines). However, one of the possible ways to provide bypass ratios of 60-70 is the use of distributed propulsion, including integrated into the airframe [8], [9].…”

Section: Discussionmentioning

confidence: 99%

Investigation of the Efficiency Limits оf the Traditional Gas Turbine Engines

Krupenich¹,

Filinov²,

Ostapyuk³

et al. 2017

IJMERR

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The article describes the results of investigation of the theoretical limits of the conventional gas turbine engines on the basis of numerical simulation using the computer-aided system "astra". The results of simulation are used to forecast the gas turbine engines' parameters as well as to determine whether the potentialities of the conventional gas turbine engines are exhausted or not. The approaches to increasing the efficiency of propulsion unit and the thermogasdynamic cycle are suggested.

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“…It denotes a serial system where electric power is produced by a generator driven by a combustion engine typically a gas-turbine. Efficiency improvement in the propulsion system results notably from the advantage that the gas-turbine operation is now decoupled from the operational constraints of the propulsor [9,13]. The system efficiency and mass can consequently be optimized by operating the gas-turbine and the propulsor close to their peak efficiency.…”

Section: Serial Systemmentioning

confidence: 99%

“…Superconductivity is considered as an enabling technology for electric drive application to transport aircraft [13,38,39]. Through the utilization of High-Temperature Superconducting (HTS) materials, the gravimetric specific power and the efficiency of the electrical component can be significantly improved.…”

Section: Superconductivitymentioning

confidence: 99%

“…The challenge of HTS application for transport aircraft lies essentially on the requirement to operate at cryogenic temperature and the resulting complex integration of the cooling system. Instead of using fossil fuels to operate the aircraft, the utilization of cryogenic fuel such as liquid hydrogen can result in strong synergies with the layout of HTS electrical system as the coolant is already available [10,13,39]. Handling safety related issues [43], the negative integration impacts of the cryogenic tank on aircraft design [44] and the infrastructural challenges to supply the liquid hydrogen to the operated airports all are issues that remain unresolved [45,46].…”

Section: Superconductivitymentioning

confidence: 99%

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Electric Drives for Propulsion System of Transport Aircraft

Pornet

2016

Encyclopedia of Aerospace Engineering

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Following the hybridization or complete electrification strategy of the electric drive pursued on terrestrial vehicles, the aviation industry is considering with great attention the application of electrical technology and power electronics for transport aircraft. The growing interest towards electric application in transport aircraft is driven by the ambitious targets for aviation declared by Europe and by the United-States of America and is motivated by the growing evidence that evolutionary improvement of the technologies might not be sufficient to fulfill these targets. As a result, the introduction of disruptive technologies turns out to be essential. With respect to the progress and perspective in electrical technology, electric drive applications to transport aircraft reveals itself to be a promising field in view of meeting the future goals.The focus of this chapter is the assessment of the electrification of the propulsion system of transport aircraft. While aiming for the ultimate goal of universally-electric aircraft, hybrid-electric approach will be first necessary to match the requirement of aircraft propulsion system and the development pace of the electrical components technology. The combinatorial variety of hybrid-electric and universally-electric propulsion system topology considered for transport aircraft application as well as key enabling technologies are first reviewed. A compendium of hybrid-electric and universally-electric advanced aircraft concepts is then proposed to obtain a notion of the cloud of aircraft configurations and electric drive options investigated up to this point in time. Finally, the integrated prospects of hybrid-electric aircraft are investigated to establish the feasibility of hybrid-electric aircraft for future market segments.Keywords: Hybrid-electric aircraft, Universally-electric aircraft, Hybrid-electric propulsion topology, Battery-fuel hybrid propulsion system, Aircraft conceptual design, Aircraft Sizing, Aircraft Performance IntroductionFollowing the hybridization or complete electrification strategy of the electric drive pursued on terrestrial vehicles, the aviation industry is considering with great attention the application of electrical technology and power electronics for transport aircraft. The growing interest towards electric application in transport aircraft is driven first by the ambitious

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Turbo-electric distributed propulsion – opportunities, benefits and challenges

Cited by 23 publications

References 15 publications

Performance analysis of an electrically assisted propulsion system for a short-range civil aircraft

Performance analysis of an electrically assisted propulsion system for a short-range civil aircraft

Investigation of the Efficiency Limits оf the Traditional Gas Turbine Engines

Electric Drives for Propulsion System of Transport Aircraft

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