A review of liquid hydrogen aircraft and propulsion technologies

Tiwari, Saurav; Pekris, Michael J.; Doherty, John J.

doi:10.1016/j.ijhydene.2023.12.263

Cited by 11 publications

(7 citation statements)

References 91 publications

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“…This covers purely electric as well as hybrid and hydrogen based powertrains. Thereby, many publications focus on the aircraft design process such as de Vries [8] and Moebs et al [23], technological aspects like Sahoo et al [30], Adler et al [2] and Tiwari et al [35], as well as nominal performance, efficiency and environmental impact of various novel propulsion concepts, as Mukhopadhaya et al [18], Zumegen et al [36] and Cinar et al [7] . Besides nominal characteristics, consideration of off-nominal system behaviour in the presence of system failures is fundamentally important.…”

Section: Research and Demarcation Of This Workmentioning

confidence: 99%

A simplified automated approach for a preliminary safetyassessment of distributed electric and hybrid propulsionsystems

Albrecht,

Siegel,

Strohmayer

2024

Preprint

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The environmental impact of disruptive aircraft and propulsion system architectures are investigated in many studies. Different energy generation and storage paths, in conjunction with the distributed propulsion systems are evaluated. The complexity of those hybrid powertrains increases significantly. As, the safety impact on aircraft level is not always obvious it has to be analyzed already in a preliminary design stage. Within this work a method shall be introduced that allows a simplified automated safety assessment of any powertrain architecture. All combinations of single and multiple failures are identified and a combined failure rate is derived. As the suitability of a component failure rate is suitable depends on the analysis of its intended function. Therefore, the component failure impact has to be evaluated on aircraft level. A selection of metrics for top-level-aircraft functions, as introduced by Jézégou is used to implement an impact driven analysis for each relevant failure case. The impact on aircraft level is calculated using handbook methods. The metrics used assess the adverse effects on climb performance, lateral controllability and range degradation. For all failure combinations these effects can be validated against requirements imposed on the configuration. The configurations used for the assessment exemplarily were developed within the GNOSIS project. Results show the necessity for a reevaluation of either the architecture or the component failure rate. The method allows an early detection of configuration specific shortcomings of complex hybrid powertrain architectures, for the chosen metrics, already in a preliminary aircraft design stage.

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Section: Research and Demarcation Of This Workmentioning

confidence: 99%

A simplified automated approach for a preliminary safetyassessment of distributed electric and hybrid propulsionsystems

Albrecht,

Siegel,

Strohmayer

2024

Preprint

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“…Specifically, for the cryo-compressed gaseous case, tanks should be designed to bear very high internal pressure levels, introducing possible severe structural weight penalties and raising concerns about safety; hence, this solution tends to be discarded for aeronautical applications [31,56]. Internal pressures for cryogenic liquid hydrogen are significantly less critical, but the tank's material should still be robust to embrittlement [58,59]. Embrittlement causes a reduction in material properties (e.g., material yield stress); thus, the reliability of the tanks is a primary goal in safely storing hydrogen.…”

Section: H 2 Storage Systemsmentioning

confidence: 99%

“…Embrittlement causes a reduction in material properties (e.g., material yield stress); thus, the reliability of the tanks is a primary goal in safely storing hydrogen. Accordingly, the choice of high strength-to-weight ratio material is relevant for proper tank design; materials such as aluminum alloys, composite materials, stainless steel, and titanium alloys can be ideal candidates to guarantee adequate strength-to-weight ratio at cryogenic temperature [59]. Liquid hydrogen, selected for the application discussed in this study, allows for increases in volumetric density and can be stored at a pressure close to ambient pressure, as depicted in Figure 2.…”

Section: H 2 Storage Systemsmentioning

confidence: 99%

“…The skin represents a separator between the insulant material and the external volume surrounding the tank, the insulant material aims at increasing the thermal resistivity in order to reduce the heat flow affecting the hydrogen state, and the structural part of the tank aims at bearing the loads (e.g., due to the internal pressure) and should be made of a material that exhibits a high strength-to-weight ratio. Typical materials that can be used for structural walls range from aluminum to composite [31,59]. Currently, there are different ways to insulate the tank: (i) closed cell foam, (ii) multilayer insulation.…”

Section: H 2 Storage Systemsmentioning

confidence: 99%

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Preliminary Performance Analysis of Medium-Range Liquid Hydrogen-Powered Box-Wing Aircraft

Palaia,

Abu Salem,

Carrera

2024

Aerospace

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This paper proposes a performance analysis of a medium-range airliner powered by liquid hydrogen (LH2) propulsion. The focus is on operating performance in terms of achievable payload and range. A non-conventional box-wing architecture was selected to maximize operating performance. An optimization-based multidisciplinary design framework was developed to retrofit a baseline medium-range box-wing aircraft by designing and integrating the fuel tanks needed to store the LH2; several solutions were investigated for tank arrangement and layout by means of sensitivity analyses. As a main outcome, a performance analysis of the proposed LH2-powered box-wing aircraft is provided, highlighting the impact of the introduction of this energy carrier (and the integration of the related tank systems) on aircraft operating performance; a comparative study with respect to a competitor LH2-retrofitted tube-and-wing aircraft is also provided, to highlight the main possible operating differences between the two architectures. The findings reveal that the retrofitted box-wing can achieve long-range flights at the cost of a substantially reduced payload, mainly due to the volume limitations imposed by the installation of LH2 tanks, or it can preserve payload capacity at the expense of a significant reduction in range, as the trade-off implies a reduction in on-board LH2 mass. Specifically, the studied box-wing configuration can achieve a range of 7100 km transporting 150 passengers, or shorter ranges of 2300 km transporting 230 passengers. The competitor LH2-retrofitted tube-and-wing aircraft, operating in the same category and compatible with the same airport apron constraints, could achieve a distance of 1500 km transporting 110 passengers.

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“…It is generally expected that hydrogen could replace kerosene in jet engines of large aircrafts. For this reason, many analyses in the literature concern the use of liquid hydrogen [22]. Currently, the use of such a drive is primarily associated with the problem of fuel storage, because it requires a low temperature of 20 K [23,24].…”

Section: Introductionmentioning

confidence: 99%

Gas Temperature Distribution in the Combustion Chamber of a GTM400 MOD Turbojet Engine Powered by JET A-1 Fuel and Hydrogen

Brodzik

2024

Energies

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Research on engine operation using hydrogen may enable appropriate optimization of thrust, and therefore performance, related to its potential use in aircraft. It is particularly important as the share of hydrogen in combustion affects the reduction of combustion products such as carbon dioxide, carbon monoxide, nitrogen oxide, hydrocarbons, and solid matter. This is in line with the new requirements regarding the increased supply of sustainable aviation fuels (SAFs) and the related changes in emissions, i.e., reducing the harmful impact of exhaust gases on the environment. This paper presents the results of measurements carried out in the GTM400 MOD turbojet engine. Based on the research performed, the impact of hydrogen and aviation kerosene combustion on selected engine parameters is presented. The paper shows changes in the rotational speed and volume flow of JET A-1 fuel as a function of engine operation time. Changes in temperature measured at the edge of the flame tube were also examined. The tests confirmed that the combustion chamber worked correctly in the selected area in the range of the tested fuel mixtures. After incorporating hydrogen into the combustion process, the consumption of traditional JET A-1 fuel was significantly reduced.

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A review of liquid hydrogen aircraft and propulsion technologies

Cited by 11 publications

References 91 publications

A simplified automated approach for a preliminary safetyassessment of distributed electric and hybrid propulsionsystems

A simplified automated approach for a preliminary safetyassessment of distributed electric and hybrid propulsionsystems

Preliminary Performance Analysis of Medium-Range Liquid Hydrogen-Powered Box-Wing Aircraft

Gas Temperature Distribution in the Combustion Chamber of a GTM400 MOD Turbojet Engine Powered by JET A-1 Fuel and Hydrogen

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