Review of the hybrid gas - electric aircraft propulsion systems versus alternative systems

Kuśmierek, Agata; Galiński, Cezary; Stalewski, Wieńczysław

doi:10.1016/j.paerosci.2023.100925

Cited by 11 publications

(3 citation statements)

References 55 publications

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“…The topic of aeronautical hybrid electric propulsion systems is thoroughly summarized in several review papers [18][19][20][21], and new interesting works are frequently emerging [22][23][24][25][26][27][28][29]. The main purpose of this paper is to present the methodology of designing a hybrid, gas-electric multi-engine propulsion system implemented by the Warsaw University of Technology.…”

Section: Motivation and Objectivementioning

confidence: 99%

Analysis Leading to the Design of a Hybrid Gas-Electric Multi-Engine Testbed

Kuśmierek,

Grzeszczyk,

Strohmayer

et al. 2023

Aerospace

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Given the increase in air traffic, the main challenges in aircraft design are in-flight emissions and noise heard by the community. These problems have thus far been solved by incremental improvements in aerodynamics, engine technology and operation. To dramatically reduce aviation’s carbon footprint towards an environmentally friendly air transport system, alternative propulsion concepts are one of the promising areas of research and first applications. In this context, the goal of integrating a hybrid-electric powertrain with a suitable airframe is to increase efficiency while reducing in-flight emissions, reduce noise for the community, drive down direct operating costs and increase reliability. This article presents an inexpensive approach to testing small, manned aircraft with a hybrid fuel–electric propulsion system. First, the design assumptions of the research flying platform are presented. Next, modifications of the existing two-seater glider are analyzed. These modifications are necessary to fit the fuel–electric hybrid propulsion system. The analysis allows us to select the elements of an appropriate hybrid electric system. It also shows that this type of small experimental propulsion system can be mounted on a two-seater aerobatic glider without significant structural modifications and still comply with the most important points of the Certification Standard-22. Finally, the design of the ground test stand for the propulsion system is described. It is believed that a thorough examination of the propulsion system on the ground will reveal both the advantages and disadvantages of the system. This should facilitate the successful installation of the system under study on a flying aircraft.

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Section: Motivation and Objectivementioning

confidence: 99%

Analysis Leading to the Design of a Hybrid Gas-Electric Multi-Engine Testbed

Kuśmierek,

Grzeszczyk,

Strohmayer

et al. 2023

Aerospace

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“…In this context, specific attention is being devoted to research into non-conventional solutions for the integration of the propulsion system, involving two different interconnected technological threads. From a general point of view, new types of propulsion systems are under investigation, and technologies involving new fuels, such as hydrogen [11][12][13][14][15][16][17][18] or sustainable aviation fuels [19][20][21][22], or electric and hybrid-electric powertrains [23][24][25][26][27][28][29][30][31][32], are under development to provide breakthrough forward advancements in the field. In addition to these important innovations, and in a way that is generally complementary, non-conventional powertrain/airframe integrations are increasingly being investigated since, either as standalone or in combination with previous new power supply concepts, they can contribute to general improvements in aircraft performance, with significant implications for reducing environmental impact.…”

Section: Introductionmentioning

confidence: 99%

A Review of Novel and Non-Conventional Propulsion Integrations for Next-Generation Aircraft

Abu Salem,

Palaia,

Bravo-Mosquera

et al. 2024

Designs

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The aim of this review paper is to collect and discuss the most relevant and updated contributions in the literature regarding studies on new or non-conventional technologies for propulsion–airframe integration. Specifically, the focus is given to both evolutionary technologies, such as ultra-high bypass ratio turbofan engines, and breakthrough propulsive concepts, represented in this frame by boundary layer ingestion engines and distributed propulsion architectures. The discussion focuses mainly on the integration effects of these propulsion technologies, with the aim of defining performance interactions with the overall aircraft, in terms of aerodynamic, propulsive, operating and mission performance. Hence, this work aims to analyse these technologies from a general perspective, related to the effects they have on overall aircraft design and performance, primarily considering the fuel consumption as a main metric. Potential advantages but also possible drawbacks or detected showstoppers are proposed and discussed with the aim of providing as broad a framework as possible for the aircraft design development roadmap for these emerging propulsive technologies.

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“…The mission profile and the means of transportation could have an impact on the results and this study focuses on vertical take-off and landing (VTOL) aircraft as they are the most demanding in terms of energy when expressed in terms of payload-distance. VTOL aircraft are also often considered in studies analyzing the opportunity to switch from fossil jet fuel to more disruptive energy vectors, such as BE and/or H 2 [4][5][6]. Since our study focuses on VTOL, the conclusions might not apply to large aircraft [7].…”

Section: Introductionmentioning

confidence: 99%

Techno-Economic Comparison of Low-Carbon Energy Carriers Based on Electricity for Air Mobility

Jarin,

Beddok,

Haritchabalet

2024

Energies

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The decarbonization of air mobility requires the decarbonization of its energy. While biofuels will play an important role, other low-carbon energy carriers based on electricity are considered, such as battery electrification and liquid hydrogen (LH2) or eFuel, a hydrogen-based energy carrier. Each energy carrier has its own conversion steps and losses and its own integration effects with aircraft. These combinations lead to different energy requirements and must be understood in order to compare their cost and CO2 emissions. Since they are all electricity-based, this study compares these energy carriers using the well-to-rotor methodology when applied to a standard vertical take-off and landing (VTOL) air mobility mission. This novel approach allows one to understand that the choice of energy carrier dictates the propulsive system architecture, leading to integration effects with aircraft, which can significantly change the energy required for the same mission, increasing it from 400 to 2665 kWh. These deviations led to significant differences in CO2 emissions and costs. Battery electrification is impacted by battery manufacturing but has the lowest electricity consumption. This is an optimum solution, but only until the battery weight can be lifted. In all scenarios, eFuel is more efficient than LH2. We conclude that using the most efficient molecule in an aircraft can compensate for the extra energy cost spent on the ground. Finally, we found that, for each of these energy carriers, it is the electricity carbon intensity and price which will dictate the cost and CO2 emissions of an air mobility mission.

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Review of the hybrid gas - electric aircraft propulsion systems versus alternative systems

Cited by 11 publications

References 55 publications

Analysis Leading to the Design of a Hybrid Gas-Electric Multi-Engine Testbed

Analysis Leading to the Design of a Hybrid Gas-Electric Multi-Engine Testbed

A Review of Novel and Non-Conventional Propulsion Integrations for Next-Generation Aircraft

Techno-Economic Comparison of Low-Carbon Energy Carriers Based on Electricity for Air Mobility

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