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Artículos de revistas sobre el tema "Combustion hydrogène"

Autor: Grafiati

Publicado: 29 de marzo de 2025

Última modificación: 31 de julio de 2025

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1

Guénan, Karine. "L’avion à hydrogène ZEROe : défis technologiques et impacts sur l’écosystème." Annales des Mines - Réalités industrielles Mai 2024, no. 2 (2024): 99–103. http://dx.doi.org/10.3917/rindu1.242.0099.

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L’aviation, symbole de mobilité et de rapprochement, doit réinventer son futur, pour répondre aux exigences de neutralité carbone d’ici 2050. L’hydrogène se présente comme une solution d’avenir pour la décarbonation de nombreuses industries. Cependant, son adoption dans l’aéronautique nécessitera des avancées majeures, de la production et distribution à grande échelle d’hydrogène vert, alimentées par les énergies renouvelables, à la conception de réservoirs cryogéniques sécurisés, en passant par l’adaptation des équipements et infrastructures aéroportuaires. Airbus se positionne en champion de

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2

Mahfoudi, El-Ahcene, Abderrahmane Gahmousse, Athmane Harizi, Kamel Talbi, and Abdellah Hadjadj. "Simulation numérique de l’écoulement compressible supersonique Application aux tuyères propulsives à combustible liquide hydrogène." Journal of Renewable Energies 15, no. 3 (2023): 365–72. http://dx.doi.org/10.54966/jreen.v15i3.327.

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Ce travail porte sur la simulation numérique de l’écoulement supersonique adapté dans les tuyères propulsives où le gaz d’essai supposé parfait est le gaz de combustion de l’Hydrogène. Il vise à déterminer les paramètres de l’écoulement Eulérien supersonique dans la tuyère convergente divergente. La méthode numérique utilisée pour la résolution de l’écoulement est basée sur une approche des volumes finis en coordonnées généralisées. L’intégration du système pour les équations de conservation d’Euler s’effectue sur un volume élémentaire quadrilatère. Dans cette étude, le traitement des flux con

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3

Studer, Etienne, Danièle Abdo, Sonia Benteboula, et al. "Sûreté des réacteurs : la connaissance du risque hydrogène enrichie de 20 ans de R&D." Revue Générale Nucléaire, no. 1 (January 2018): 48–53. http://dx.doi.org/10.1051/rgn/20181048.

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Le CEA s’est doté d’une compétence forte pour comprendre, modéliser et prévenir le risque hydrogène dans les installations nucléaires. À partir du milieu des années 1990, une approche couplée numérique et expérimental a été mise en oeuvre pour atteindre ces objectifs : le projet TONUS pour se doter d’outils numériques pour traiter de la distribution et de la combustion de l’hydrogène et le projet MISTRA pour alimenter ces modèles numériques en données expérimentales « CFD grade » pour la distribution de l’hydrogène et l’efficacité des moyens de prévention. Ces connaissances et ces outils ont c

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4

De Giorgi, M. G., G. Cinieri, G. Marseglia, Z. Ali Shah, and Ghazanfar Mehdi. "Combustion Efficiency of Carbon-neutral Fuel using Micro-Combustor Designed for Aerospace Applications." Journal of Physics: Conference Series 2716, no. 1 (2024): 012091. http://dx.doi.org/10.1088/1742-6596/2716/1/012091.

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Abstract Recent advancements in the field of micro combustor research are growing for achieving high-performance systems in micro power generation and microelectromechanical devices. To mitigate the hazardous emissions from carbon fuels, as an alternative, zero-carbon-free fuels ammonia, and hydrogen are being explored in micro combustion processes. The distinctive feature of a micro combustor lies in its significantly higher area to volume ratio in comparison with traditional combustion systems, leading to accelerated combustion reaction rates. However, the small size of micro combustors pose

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5

Serbin, Serhiy, Mykola Radchenko, Anatoliy Pavlenko, Kateryna Burunsuz, Andrii Radchenko, and Daifen Chen. "Improving Ecological Efficiency of Gas Turbine Power System by Combusting Hydrogen and Hydrogen-Natural Gas Mixtures." Energies 16, no. 9 (2023): 3618. http://dx.doi.org/10.3390/en16093618.

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Currently, the issue of creating decarbonized energy systems in various spheres of life is acute. Therefore, for gas turbine power systems including hybrid power plants with fuel cells, it is relevant to transfer the existing engines to pure hydrogen or mixtures of hydrogen with natural gas. However, significant problems arise associated with the possibility of the appearance of flashback zones and acoustic instability of combustion, an increase in the temperature of the walls of the flame tubes, and an increase in the emission of nitrogen oxides, in some cases. This work is devoted to improvi

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6

Lee, Jaeyoung, Chang Bum Sohn, Young Sik Jeong, and Young Bae Kim. "A Numerical Analysis of Premixed Hydrogen–Methane Flame with Three Different Header Types of Combustor." Fire 7, no. 10 (2024): 361. http://dx.doi.org/10.3390/fire7100361.

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This study investigated the impact of thin-flame combustor design on hydrogen flame characteristics and combustion performance through numerical simulations. Differences in the flame shape and combustibility between pure methane and pure hydrogen combustion were analyzed. Three combustor header shapes (flat, concave, and convex) were modeled to assess the influence of header shape on flame behavior. The results revealed distinct flow patterns, with the concave header promoting strong central flows and the convex header dispersing the flow outward. Temperature field analysis indicated that the

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7

Franco, Alessandro, and Michele Rocca. "Industrial Decarbonization through Blended Combustion of Natural Gas and Hydrogen." Hydrogen 5, no. 3 (2024): 519–39. http://dx.doi.org/10.3390/hydrogen5030029.

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The transition to cleaner energy sources, particularly in hard-to-abate industrial sectors, often requires the gradual integration of new technologies. Hydrogen, crucial for decarbonization, is explored as a fuel in blended combustions. Blending or replacing fuels impacts combustion stability and heat transfer rates due to differing densities. An extensive literature review examines blended combustion, focusing on hydrogen/methane mixtures. While industrial burners claim to accommodate up to 20% hydrogen, theoretical support is lacking. A novel thermodynamic analysis methodology is introduced,

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8

Feng, Zhenzhen, Xiaojing Tian, Liangliang Xu, Xi Xia, and Fei Qi. "Experimental Investigation of Pure Hydrogen Flame in a Matrix Micro-Mixing Combustor." Aerospace 12, no. 6 (2025): 464. https://doi.org/10.3390/aerospace12060464.

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Pure hydrogen combustion is a critical pathway to achieving zero-carbon emissions for the gas turbine industry. Micro-mixing combustion is one of the most widely attractive hydrogen combustion methods in gas turbines. This study investigates pure hydrogen flame in a 3 × 3 matrix micro-mix combustor. The setup includes nine micro-mix injectors, each equipped with a bluff body and a hydrogen injection tube. The OH* chemiluminescence imaging and PIV (Particle Image Velocimetry) techniques were employed to visualize the single- and triple-flame morphology and flow field under various operating con

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9

Wang, Kefu, Feng Li, Tao Zhou, and Yiqun Ao. "Numerical Study of Combustion and Emission Characteristics for Hydrogen Mixed Fuel in the Methane-Fueled Gas Turbine Combustor." Aerospace 10, no. 1 (2023): 72. http://dx.doi.org/10.3390/aerospace10010072.

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The aeroderivative gas turbine is widely used as it demonstrates many advantages. Adding hydrogen to natural gas fuels can improve the performance of combustion. Following this, the effects of hydrogen enrichment on combustion characteristics were analyzed in an aeroderivative gas turbine combustor using CFD simulations. The numerical model was validated with experimental results. The conditions of the constant mass flow rate and the constant energy input were studied. The results indicate that adding hydrogen reduced the fuel residues significantly (fuel mass at the combustion chamber outlet

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10

Tamang, Sajan, and Heesung Park. "Numerical investigation on the dry low NOx of hydrogen combustion." Journal of Physics: Conference Series 2968, no. 1 (2025): 012009. https://doi.org/10.1088/1742-6596/2968/1/012009.

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Abstract Globally, energy is predominantly generated through the combustion of fossil fuels. However, the emissions from these fuels severely impact the ecological balance and environment. As a result, there is a growing emphasis on clean and renewable energy sources as alternatives. Hydrogen is a promising and clean energy source for gas turbines, transportation, and industrial applications. Nevertheless, due to significant differences in hydrogen’s thermophysical properties, it cannot be directly integrated into conventional combustion systems. Therefore, a specialized micromix combustion mo

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11

Huang, Juan-Chen, Yu-Hsuan Lai, Jeng-Shan Guo, and Jaw-Yen Yang. "Simulation of Two-Dimensional Scramjet Combustor Reacting Flow Field Using Reynolds Averaged Navier-Stokes WENO Solver." Communications in Computational Physics 18, no. 4 (2015): 1181–210. http://dx.doi.org/10.4208/cicp.190115.210715s.

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AbstractThe non-equilibrium chemical reacting combustion flows of a proposed long slender scramjet system were numerically studied by solving the turbulent Reynolds averaged Navier-Stokes (RANS) equations. The Spalart-Allmaras one equation turbulence model is used which produces better results for near wall and boundary layer flow field problems. The lower-upper symmetric Gauss-Seidel implicit scheme, which enables results converge efficiently under steady state condition, is combined with the weighted essentially non-oscillatory (WENO) scheme to yield an accurate simulation tool for scramjet

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12

Waitz, Ian A., Gautam Gauba, and Yang-Sheng Tzeng. "Combustors for Micro-Gas Turbine Engines." Journal of Fluids Engineering 120, no. 1 (1998): 109–17. http://dx.doi.org/10.1115/1.2819633.

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The development of a hydrogen-air microcombustor is described. The combustor is intended for use in a 1 mm2 inlet area, micro-gas turbine engine. While the size of the device poses several difficulties, it also provides new and unique opportunities. The combustion concept investigated is based upon introducing hydrogen and premixing it with air upstream of the combustor. The wide flammability limits of hydrogen-air mixtures and the use of refractory ceramics enable combustion at lean conditions, obviating the need for both a combustor dilution zone and combustor wall cooling. The entire combus

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13

Kim, Jonghyun, and Jungsoo Park. "Conceptual Approach to Combustor Nozzle and Reformer Characteristics for Micro-Gas Turbine with an On-Board Reforming System: A Novel Thermal and Low Emission Cycle." Sustainability 12, no. 24 (2020): 10558. http://dx.doi.org/10.3390/su122410558.

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In order to implement moderate or intensive low oxygen dilution (MILD) combustion, it is necessary to extend the flame stability and operating range. In the present study, the conceptual designs of a combustor single nozzle and reformer were numerically suggested for a micro-gas turbine with an on-board reformer. The target micro-gas turbine achieved a thermal power of 150 kW and a turbine inlet temperature (TIT) of 1200 K. Studies on a nozzle and reformer applying an open-loop concept have been separately conducted. For the nozzle concept, a single down-scaled nozzle was applied based on a re

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14

Goldfeld, Marat, and Alexey Starov. "Scheme of Hydrogen Ignition in Duct with Shock Waves." Siberian Journal of Physics 9, no. 2 (2014): 116–27. http://dx.doi.org/10.54362/1818-7919-2014-9-2-116-127.

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In article results of the analysis of processes of self-ignition and combustion propagation are given in the multi-injector combustion chamber with high supersonic speeds of an air flow. It is established that fuel ignition at high Mach numbers, bringing to flame propagation on all volume of combustor and combustion stabilization, happens not in recirculation area behind a step, and in the field of interaction of shock waves with an boundary layer on walls or behind this area downstream near an angular point of the combustion chamber. The scheme of development of process of combustion in the c

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15

Ma, Yi, Wenhua Yuan, Shaomin Zhao, and Hongru Fang. "Premixed Combustion Characteristics of Hydrogen/Air in a Micro-Cylindrical Combustor with Double Ribs." Energies 17, no. 20 (2024): 5165. http://dx.doi.org/10.3390/en17205165.

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Hydrogen is a promising zero-carbon fuel, and its application in the micro-combustor can promote carbon reduction. The structural design of micro-combustors is crucial for combustion characteristics and thermal performance improvement. This study investigates the premixed combustion characteristics of hydrogen/air in a micro-cylindrical combustor with double ribs, using an orthogonal design method to assess the impact of various geometric parameters on thermal performance. The results indicate that the impact of rib height, rib position, and inclined angle is greater than rib width and their i

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16

Carrier, D. M., and R. J. Wetton. "Prediction of Combustion Performance of Aviation Kerosines Using a Novel Premixed Flame Technique." Journal of Engineering for Gas Turbines and Power 110, no. 1 (1988): 100–104. http://dx.doi.org/10.1115/1.3240071.

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A novel method for predicting aviation fuel combustion performance has been developed in which the sooting point of a premixed flame is detected automatically. Comparisons with full-scale combustor data confirm that the technique is a more realistic index of combustion quality than Smoke Point or hydrogen content.

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17

Zvada, Branislav, Radovan Nosek, Peter Ďurčanský, Andrej Kapjor, and Nikola Kantová Čajová. "Numerical Predictive Combustion Model of Hydrogen Enriched Natural Gas." MATEC Web of Conferences 369 (2022): 03003. http://dx.doi.org/10.1051/matecconf/202236903003.

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Hydrogen was established as one of the main pillars of energy stability in the Europe Union. One of the ways how to achieve this goal is natural gas enriched with hydrogen. Due to this is very important to know the properties of this fuel and its behaviour during combustion. The main scope of the research is to provide a better understanding of the emissions, efficiency, and performance of the heat source when combusting hydrogen and gas fuel mixture. In this paper is described hydrogen characteristics, hydrogen fuel preparation, an overview of gas fuel combustion in gas appliances with the hy

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18

Abhijeet, Chougule, and R. Sonde Ramakrishna. "Design and Empirical Inquisition of Catalytic Combustor for Methanol Steam Reformer in HT-PEM Fuel Cell Systems." International Journal of Engineering and Advanced Technology (IJEAT) 9, no. 4 (2020): 1776–82. https://doi.org/10.35940/ijeat.D6836.049420.

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Steam reforming of methanol is a basic endothermic reaction. For which, a separate external system is required for generation of heat. The reaction speeds are controlled by operating temperature and heat transfer rate to the reactor. This operating temperature has a very narrow window of operation. It is therefore extremely important to have a system that generates controlled combustion based stable heat for providing required heat to reformer. A design of catalytic combustor was developed and analyzed for methanol steam reformer. The packed bed of combustion catalyst provides active sites for

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19

Stępień, Zbigniew, and Wiesława Urzędowska. "Tłokowe silniki spalinowe zasilane wodorem – wyzwania." Nafta-Gaz 77, no. 12 (2021): 830–40. http://dx.doi.org/10.18668/ng.2021.12.06.

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W artykule opisano potencjał wodoru jako kluczowego nośnika energii w przyszłości. Wskazano przy tym, że spośród znanych paliw alternatywnych wodór stanowi najlepsze rozwiązanie w zakresie ograniczenia lub nawet całkowitego wyeliminowania niebezpiecznych emisji, w tym GHG z pojazdów. Dlatego wodór jest powszechnie postrzegany jako perspektywiczne, zrównoważone paliwo, i to zarówno do zasilania tłokowych silników spalinowych, jak i ogniw paliwowych. Ze względu na zaawansowany rozwój tłokowych silników spalinowych i ich szeroką dostępność mogą one pełnić rolę technologii pomostowej dla szerokieg

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20

Fąfara, Jean-Marc, and Norbert Modliński. "Computational Fluid Dynamics (CFD) Assessment of the Internal Flue Gases Recirculation (IFGR) Applied to Gas Microturbine in the Context of More Hydrogen-Enriched Fuel Use." Energies 16, no. 18 (2023): 6703. http://dx.doi.org/10.3390/en16186703.

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Renewable energy is a promising substitute for fossil fuels when corelated with P2G technology. To optimise P2G efficiency, there is a need to increase hydrogen fraction in the fuel stream. Simultaneously gas microturbines are widely applied in many industry sectors. These devices are often equipped with diffusion combustors. This situation was investigated in this paper. The P2G and gas microturbines may be integrated together in the future leading to the application of hydrogen-enriched fuel. Hydrogen-enriched fuel causes increase in combustion temperature and velocity. In a nonadapted combu

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21

Naeemi, Saeed, and Seyed Abdolmehdi Hashemi. "Numerical investigations on the liftoff velocity of H2-air premixed combustion in a micro-cylindrical combustor with gradually changed section area." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 234, no. 17 (2020): 3497–508. http://dx.doi.org/10.1177/0954406220914925.

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Sustaining and stabilizing flames are crucial issues in micro-combustion. In some micro-electro-mechanical systems such as the micro-thermophotovoltaic system, the flame should be formed in the combustion chamber, not outside it (combustion without liftoff). So, study of the liftoff phenomenon is important and vital in these systems. The aim of this study is to evaluate effect of changing combustor section area on the critical liftoff velocity in a micro-cylindrical combustor. For this purpose, the critical liftoff velocities are numerically identified for four combustor configurations (conver

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22

Kanik Mittal and Sachin Srivastava. "SCRAMJET: Future High Speed Aircraft." Acceleron Aerospace Journal 3, no. 7 (2024): 785. https://doi.org/10.61359/11.2106-2476.

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In the current era of technological advancement, the scramjet has become one of the most conventional engines for achieving supersonic speeds in aircraft. The scramjet comprises three basic components: the inlet, combustor, and nozzle. Various fuels, such as Kerosene, JP-7, JP-8, hydrocarbon-based fuels, and hydrogen, have been used in scramjets, demonstrating distinct performance characteristics. Tests have shown that hydrocarbon-fueled scramjet engines can achieve a Mach number range of 3.5 to 7, while solid-fueled scramjets have the potential to achieve combustion efficiencies of 0.7–0.9. F

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23

Yang, Xiao, Zhihong He, Lei Zhao, Shikui Dong, and Heping Tan. "Effect of Channel Diameter on the Combustion and Thermal Behavior of a Hydrogen/Air Premixed Flame in a Swirl Micro-Combustor." Energies 12, no. 20 (2019): 3821. http://dx.doi.org/10.3390/en12203821.

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Improving the flame stability and thermal behavior of the micro-combustor (MC) are major challenges in microscale combustion. In this paper, the micro combustions of an H2/air premixed flame in a swirl MC with various channel diameters (Din = 2, 3, 4 mm) were analyzed based on an established three-dimensional numerical model. The effects of hydrogen mass flow rate, thermal conductivity of walls, and the preferential transport of species were investigated. The results indicated that the flame type was characterized by the presence of two recirculation zones. The flame was anchored by the recirc

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24

Cameretti, Maria Cristina, Roberta De Robbio, Vincenzo Ferrara, and Raffaele Tuccillo. "Performance and Emissions Evaluation of a Turbofan Burner with Hydrogen Fuel." Aerospace 12, no. 3 (2025): 231. https://doi.org/10.3390/aerospace12030231.

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This paper examines the changes in the performance level and pollutant emissions of a combustion chamber for turbofan engines. Two different fuels are compared: a conventional liquid fuel of the JET-A (kerosene) class and a hydrogen-based gaseous fuel. A turbofan engine delivering a 70 kN thrust at cruise conditions and 375 kN thrust at take-off is considered. The comparison is carried out by investigating the combustion pattern with different boundary conditions, the latter assigned along a typical flight mission. The calculations rely on a combined approach with a preliminary lumped paramete

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25

Kim, Chae-Hyoung, and In-Seuck Jeung. "Forced Combustion Characteristics Related to Different Injection Locations in Unheated Supersonic Flow." Energies 12, no. 9 (2019): 1746. http://dx.doi.org/10.3390/en12091746.

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This work focuses on forced combustion with regards to the relationship between vent mixer models and several injection locations in unheated supersonic flow. A plasma jet torch was used to ignite the hydrogen-air mixture in a laboratory-scaled combustor duct. The flow field of the combustion was visualized with pressure and gas-sampling measurements. The vent mixers indicate good dispersion characteristics of the mixture for both parallel and normal 1 injections. However, forced combustion is dominantly governed by the injection rate toward the plasma jet (hot source) because the combustible

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Zian, Norhaslina Mat, Hasril Hasini, and Nur Irmawati Om. "Investigation of Syngas Combustion at Variable Methane Composition in Can Combustor Using CFD." Advanced Materials Research 1016 (August 2014): 592–96. http://dx.doi.org/10.4028/www.scientific.net/amr.1016.592.

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This paper describes the analysis of the fundamental effect of synthetic gas combustion in a can-type combustor using Computational Fluid Dynamic(CFD). Emphasis is given towards the effect of variation of methane to the flame profile, temperature distribution and heat flux in the combustor. In this study, the composition of hydrogen in the syngas was fixed at 30% while methane and carbon monoxide were varied. Results show that the flame temperature and NOxemissions are highly dependent on the composition of methane in the syngas fuel. Nevertheless, the overall NOxemission for all cases is rela

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27

Beita, Jadeed, Midhat Talibi, Suresh Sadasivuni, and Ramanarayanan Balachandran. "Thermoacoustic Instability Considerations for High Hydrogen Combustion in Lean Premixed Gas Turbine Combustors: A Review." Hydrogen 2, no. 1 (2021): 33–57. http://dx.doi.org/10.3390/hydrogen2010003.

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Hydrogen is receiving increasing attention as a versatile energy vector to help accelerate the transition to a decarbonised energy future. Gas turbines will continue to play a critical role in providing grid stability and resilience in future low-carbon power systems; however, it is recognised that this role is contingent upon achieving increased thermal efficiencies and the ability to operate on carbon-neutral fuels such as hydrogen. An important consideration in the development of gas turbine combustors capable of operating with pure hydrogen or hydrogen-enriched natural gas are the signific

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Beita, Jadeed, Midhat Talibi, Suresh Sadasivuni, and Ramanarayanan Balachandran. "Thermoacoustic Instability Considerations for High Hydrogen Combustion in Lean Premixed Gas Turbine Combustors: A Review." Hydrogen 2, no. 1 (2021): 33–57. http://dx.doi.org/10.3390/hydrogen2010003.

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Hydrogen is receiving increasing attention as a versatile energy vector to help accelerate the transition to a decarbonised energy future. Gas turbines will continue to play a critical role in providing grid stability and resilience in future low-carbon power systems; however, it is recognised that this role is contingent upon achieving increased thermal efficiencies and the ability to operate on carbon-neutral fuels such as hydrogen. An important consideration in the development of gas turbine combustors capable of operating with pure hydrogen or hydrogen-enriched natural gas are the signific

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29

Roga, Sukanta, and Krishna Murari Pandey. "Computational Analysis of Hydrogen-Fueled Scramjet Combustor Using Cavities in Tandem Flame Holder." Applied Mechanics and Materials 772 (July 2015): 130–35. http://dx.doi.org/10.4028/www.scientific.net/amm.772.130.

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This work presents the computational analysis of scramjet combustor using cavities in tandem flame holder by means of 3D. The fuel used by scramjet combustor with cavities in tandem flame holder is hydrogen, the fluid flow and the work is based on the species transport combustion with standard k-ε viscous model. The Mach number at inlet is 2.47 and stagnation temperature and static pressure for vitiated air are 1000K and 100kPa respectively. These computational analysis is mainly aimed to study the flow structure and combustion efficiency. The computational results are compared qualitatively a

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Teodosio, Luigi, Fabio Berni, Alfredo Lanotte, and Enrica Malfi. "1D/3D simulation procedure to investigate the potential of a lean burn hydrogen fuelled engine." Journal of Physics: Conference Series 2385, no. 1 (2022): 012085. http://dx.doi.org/10.1088/1742-6596/2385/1/012085.

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Abstract In recent years hydrogen, especially the one generated by renewable energy, is gaining increasing attention as a clean fuel to support the future mobility towards efficient and low emission solutions for propulsion systems. In this scenario, the present work deals with the virtual conversion of a single-cylinder Diesel engine, conceived for marine applications, into a hydrogen Spark Ignition (SI) unit. A simulation methodology is adopted, combining 1D and 3D Computational Fluid Dynamics (CFD) methods. First, experiments are realized on the original Diesel engine mounted on a test benc

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31

Jeong, Seung-Min, and Jeong-Yeol Choi. "Combined Diagnostic Analysis of Dynamic Combustion Characteristics in a Scramjet Engine." Energies 13, no. 15 (2020): 4029. http://dx.doi.org/10.3390/en13154029.

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In this work, the dynamic combustion characteristics in a scramjet engine were investigated using three diagnostic data analysis methods: DMD (Dynamic Mode Decomposition), STFT (Short-Time Fourier Transform), and CEMA (Chemical Explosive Mode Analysis). The data for the analyses were obtained through a 2D numerical experiment using a DDES (Delayed Detached Eddy Simulation) turbulence model, the UCSD (University of California at San Diego) hydrogen/oxygen chemical reaction mechanism, and high-resolution schemes. The STFT was able to detect that oscillations above 50 kHz identified as dominant i

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32

Oleś, Sylwia, Jakub Mularski, Dariusz Pyka, Halina Pawlak-Kruczek, and Artur Pozarlik. "Optimization of Hydrogen Supercritical Oxy-Combustion in Gas Turbines." Fuels 6, no. 1 (2025): 6. https://doi.org/10.3390/fuels6010006.

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This study investigates the combustion of hydrogen in supercritical gas turbines, emphasizing the optimization of combustor design through computational fluid dynamics (CFD) simulations. Key parameters analysed include the number of oxygen inlets, operating pressure, excess working fluid in oxygen inlets, power output, and the use of different working fluids: supercritical argon (sAr) and supercritical xenon (sXe). The results highlight how these parameters influence temperature distribution, flame stability, and overall combustion efficiency. Findings suggest that increasing the number of oxy

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33

Wang, Taiyu, Zhenguo Wang, Zun Cai, et al. "Effects of combustor geometry on the combustion process of an RBCC combustor in high-speed ejector mode." Modern Physics Letters B 33, no. 27 (2019): 1950330. http://dx.doi.org/10.1142/s0217984919503305.

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The combustion characteristics of high-speed ejector mode in a 2-dimensional strut-based RBCC (rocket-based combined cycle) combustor had been investigated numerically in a Mach 2.5 supersonic flow. The numerical approach had been validated by comparing numerical results with available experimental data. Besides, three different hydrogen-air chemical reaction mechanisms had also been compared. The effect of the combustor geometry on the combustion process was then discussed by analyzing the heat release distribution and flow field. It was found that the wall configuration, closeout angle of th

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34

Wang, Hongbo, Zhenguo Wang, Mingbo Sun, and Haiyan Wu. "Combustion modes of hydrogen jet combustion in a cavity-based supersonic combustor." International Journal of Hydrogen Energy 38, no. 27 (2013): 12078–89. http://dx.doi.org/10.1016/j.ijhydene.2013.06.132.

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35

Pinto, Bruno M., Gonçalo P. Pacheco, Miguel A. A. Mendes, and Pedro J. Coelho. "Numerical Simulation of Natural Gas/Hydrogen Combustion in a Novel Laboratory Combustor." Applied Sciences 15, no. 13 (2025): 7123. https://doi.org/10.3390/app15137123.

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Hydrogen is a promising fuel in the current transition to zero-net CO2 emissions. However, most practical combustion equipment is not yet ready to burn pure hydrogen without adaptation. In the meantime, blending hydrogen with natural gas is an interesting option. This work reports a computational study of the performance of swirl-stabilized natural gas/hydrogen flames in a novel combustion chamber design. The combustor employs an air-staging strategy, introducing secondary air through a top-mounted plenum in a direction opposite to the fuel jet. The thermal load is fixed at 5 kW, and the effec

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36

Suppandipillai, Jeyakumar, Jayaraman Kandasamy, R. Sivakumar, Mehmet Karaca, and Karthik K. "Numerical investigations on the hydrogen jet pressure variations in a strut based scramjet combustor." Aircraft Engineering and Aerospace Technology 93, no. 4 (2021): 566–78. http://dx.doi.org/10.1108/aeat-08-2020-0162.

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Purpose This paper aims to study the influences of hydrogen jet pressure on flow features of a strut-based injector in a scramjet combustor under-reacting cases are numerically investigated in this study. Design/methodology/approach The numerical analysis is carried out using Reynolds Averaged Navier Stokes (RANS) equations with the Shear Stress Transport k-ω turbulence model in contention to comprehend the flow physics during scramjet combustion. The three major parameters such as the shock wave pattern, wall pressures and static temperature across the combustor are validated with the reporte

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37

Pandey, K. M., and T. Sivasakthivel. "CFD Analysis of Mixing and Combustion of a Hydrogen Fueled Scramjet Combustor with a Strut Injector by Using Fluent Software." International Journal of Engineering and Technology 3, no. 5 (2011): 466–53. http://dx.doi.org/10.7763/ijet.2011.v3.268.

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38

Dash, Santanu Kumar, Suprava Chakraborty, Michele Roccotelli, and Umesh Kumar Sahu. "Hydrogen Fuel for Future Mobility: Challenges and Future Aspects." Sustainability 14, no. 14 (2022): 8285. http://dx.doi.org/10.3390/su14148285.

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Nowadays, the combustion of fossil fuels for transportation has a major negative impact on the environment. All nations are concerned with environmental safety and the regulation of pollution, motivating researchers across the world to find an alternate transportation fuel. The transition of the transportation sector towards sustainability for environmental safety can be achieved by the manifestation and commercialization of clean hydrogen fuel. Hydrogen fuel for sustainable mobility has its own effectiveness in terms of its generation and refueling processes. As the fuel requirement of vehicl

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39

Mahjoub, Mustafa, Aleksandar Milivojevic, Vuk Adzic, Marija Zivkovic, Vasko Fotev, and Miroljub Adzic. "Numerical analysis of lean premixed combustor fueled by propane-hydrogen mixture." Thermal Science 21, no. 6 Part A (2017): 2599–608. http://dx.doi.org/10.2298/tsci160717131m.

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A numerical investigation of combustion of propane-hydrogen mixture in a swirl premixed micro gas turbine combustor is presented. The effects of hydrogen addition into propane on temperature distribution in the combustor, reaction rates of propane and hydrogen and NOx emissions for different equivalence ratios and swirl numbers are given. The propane-hydrogen mixture of 90/10% by volume was assumed. The numerical results and measurements of NOx emissions for pure propane are compared. Excellent agreements are found for all equivalence ratios and swirl numbers, except for the highest swirl numb

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40

Medhat, Moataz, Adel Khalil, and Mohamed A. Yehia. "A Numerical Study of Decarbonizing Marine Gas Turbine Emissions Through Ammonia/Hydrogen Fuel Blends." Journal of Physics: Conference Series 2304, no. 1 (2022): 012008. http://dx.doi.org/10.1088/1742-6596/2304/1/012008.

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Abstract The employment of gas turbine in combination with diesel engines and steam generators is a well-known power generation technique in modern marines and ship propulsion. Previously, it rendered its foundations in marine industry through higher power weight ratios and lower NOx emissions if compared to pure diesel engine driven marines. As climate change concerns are becoming more serious, the decarbonization of marine combustion products is becoming of environmental concern. In the present study a modified design of the burner and combustor was suggested to allow for the longer residenc

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41

Kim, Min-Su, In-Hoi Koo, Keon-Hyeong Lee, et al. "Experimental Study on the Ignition Characteristics of Scramjet Combustor with Tandem Cavities Using Micro-Pulse Detonation Engine." Aerospace 10, no. 8 (2023): 706. http://dx.doi.org/10.3390/aerospace10080706.

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This experimental investigation focused on the ignition and combustion characteristics of a tandem cavity-based scramjet combustor with side-by-side identical cavities. This study utilized the Pusan National University-direct connect scramjet combustor (PNU-DCSC), which was capable of simulating flight conditions at Mach number 4.0–5.0 and altitudes of 20–25 km using the vitiated air heater (VAH). The combustion tests were conducted under off-design point conditions corresponding to low inlet enthalpy. It is a condition in which self-ignition does not occur, and a micro pulse detonation engine

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42

Ciani, Andrea, Mirko Bothien, Birute Bunkute, John Wood, and Gerhard Früchtel. "Superior fuel and operational flexibility of sequential combustion in Ansaldo Energia gas turbines." Journal of the Global Power and Propulsion Society 3 (October 21, 2019): 630–38. http://dx.doi.org/10.33737/jgpps/110717.

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The increasing use of renewables for energy production is also accompanied by an increasing need for flexible power production, while aiming at carbon free emissions. The potential solutions of energy storage of excess generation from renewables through hydrogen production and pre-combustion carbon capture are gaining momentum. Both scenarios require gas turbines capable of operation with hydrogen-based fuels. At the same time, the composition of natural gas considered for use within gas turbines is becoming significantly more variable due to increased use of liquefied natural gas and a wider

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43

Xi, Wenxiong, Hui Xu, Tianyang Dong, Zhiyong Lin, and Jian Liu. "Numerical Investigation of Combustion Mechanism with Multi-Position Injection in a Dual-Mode Combustor." Aerospace 10, no. 7 (2023): 656. http://dx.doi.org/10.3390/aerospace10070656.

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To improve the flame propagation, combustion stability, and uniformity of the temperature field, multi-position injection is applied in a dual-mode combustor by controlling heat release in different locations. Using the chemical reaction of the finite rate combustion model and the detailed reaction mechanism of hydrogen combustion as described by Jachimowski, the influence of different multi-position injection patterns in a dual-mode combustor is analyzed. The one-equation Large Eddy Simulation (LES) turbulence model was chosen to define the sublattice turbulent viscous terms in a three-dimens

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44

Pappa, Alessio, and Ward De Paepe. "Humidification Towards Flashback Prevention in a Classical Micro Gas Turbine: Thermodynamic Performance Assessment." E3S Web of Conferences 414 (2023): 03010. http://dx.doi.org/10.1051/e3sconf/202341403010.

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Combustion air humidification has proven to be effective to stabilize hydrogen combustion and to avoid flashback apparition in a typical micro Gas Turbine (mGT). However, both the fuel alteration and combustion air dilution will impact the cycle performance. A complete characterization of this thermodynamic impact is essential to ensure that the mGTs become cleaner, and fully flexible to fit with the expectation of future small-scale decentralized power production. Therefore, the objective of this work is twofold: the determination of the necessary dilution for combustion stabilization, depend

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45

Nishiguchi, Hironobu, Masatoshi Kodera, and Sadatake Tomioka. "Effects of the Fuel Species on the Combustion Pressure in a Two Staged Fueled Scramjet Combustor." Aerospace 12, no. 1 (2025): 66. https://doi.org/10.3390/aerospace12010066.

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Two-staged fuel injection configuration for scramjet combustors has been shown to be effective in distributing heat release in the combustor for preventing the unstart transition of the engine by suppressing peak pressure while increasing the pressure thrust. In this study, the effect of fuel species on combustion characteristics in a two-staged fueled scramjet combustor was investigated. Wall pressure measurements in a two-staged fueled scramjet combustor were conducted in a combustion wind tunnel facility with fuels having different reactivity, such as H2 and CH4. Reynolds-Averaged Navier–St

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46

SERRANO, David, Bruno WALTER, and Florence DUFFOUR. "Le moteur à combustion hydrogène, un vecteur essentiel de la transition énergétique." Machines hydrauliques, aérodynamiques et thermiques, June 2024. http://dx.doi.org/10.51257/a-v1-hy8580.

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47

Pappa, Alessio, Laurent Bricteux, Pierre Bénard, and Ward De Paepe. "Can Water Dilution Avoid Flashback on a Hydrogen-Enriched Micro-Gas Turbine Combustion?—A Large Eddy Simulations Study." Journal of Engineering for Gas Turbines and Power 143, no. 4 (2021). http://dx.doi.org/10.1115/1.4049798.

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Abstract Considering the growing interest in Power-to-Fuel, i.e., production of H2 using electrolysis to store excess renewable electricity, combustion-based technologies still have a role to play in the future of power generation. Especially in a decentralized production with small-scale cogeneration, micro-Gas Turbines (mGTs) offer great advantages related to their high adaptability and flexibility, in terms of operation and fuel. Hydrogen (or hydrogen enriched methane) combustion is well-known to lead to flame and combustion instabilities. The high temperatures and reaction rates reached in

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48

A., Shankar, Parammasivam K.M., and Subramanian Surya Narayanan. "A review on computational studies on hydrogen combustion for gas turbine applications." Aircraft Engineering and Aerospace Technology, August 27, 2024. http://dx.doi.org/10.1108/aeat-12-2023-0312.

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Purpose The purpose of this paper is to provide an overview of the computational progress in the development of hydrogen-fired gas turbines. This review aims to identify suitable combustion models, appropriate NOx chemistry mechanisms and NOx emission levels for effective utilization of hydrogen as an alternative fuel in gas turbines. Design/methodology/approach Hydrogen is recognized as a potential alternative fuel for achieving exceptionally low emissions in gas turbines. The developments in conventional, trapped vortex combustor and micromix combustors are discussed, along with various comp

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49

Jung, Junwoo, Daesik Kim, Yuangang Wang, et al. "Suppression of Combustion Oscillations in Hydrogen-Enriched Can-Type Combustors Through Fuel Staging." Journal of Engineering for Gas Turbines and Power, August 17, 2024, 1–48. http://dx.doi.org/10.1115/1.4066239.

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Abstract To achieve decarbonization in power-generating gas turbines, the technology of mixing hydrogen with natural gas is garnering significant attention. However, when blending natural gas with hydrogen, the altered combustion characteristics can lead to combustion instability in gas turbine combustors. Although fuel staging can effectively suppress combustion instability for can-type combustors, further research on mitigation strategies for hydrogen co-firing and their predictive methods is required. This study involves hydrogen co-firing experiments using a full-scale can-type combustor.

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50

Kim, Byungwook, Thanh Dam Mai, Duy-Tan Vo, et al. "Hydrogen combustion in two-stage high-pressure gas turbine—thermal and flow simulations for performance comparison with fossil fuels." International Journal of Engine Research, October 4, 2023. http://dx.doi.org/10.1177/14680874231196987.

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Hydrogen energy forms an attractive solution for reducing greenhouse gas emissions from gas turbine systems. Although hydrogen combustion has been widely studied for combustors, only a few studies have considered the combustion effect downstream of the combustor. This study conducted an integral simulation of the combustion and flow of a GE-E3 aero-engine under hydrogen fuel and compared its performance with that of representative fossil fuels such as Jet A in an aero-engine and methane in an industrial gas turbine. All simulations were conducted under a constant heat input at the combustor an

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