Literatura académica sobre el tema "Chambre de combustion aéronautique"
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Artículos de revistas sobre el tema "Chambre de combustion aéronautique":
Grisch, Frédéric, Bruno Renou, Gilles Cabot y Mourad Boukhalfa. "Métrologie optique pour l’optimisation de la combustion aéronautique… Quel avenir ?" Photoniques, n.º 84 (noviembre de 2016): 33–36. http://dx.doi.org/10.1051/photon/20168433.
Léger, Bruno, Patrick André, Guy Grienche y Gérard Schott. "Contrôle thermique de parois de chambre de combustion. Banc d'essai du laboratoire aquitain de recherche en aérothermique". Revue Générale de Thermique 35, n.º 417 (octubre de 1996): 625–30. http://dx.doi.org/10.1016/s0035-3159(96)80025-0.
Vernocchi, Virginia, Marco Brunoldi, Silvia G. Danelli, Franco Parodi, Paolo Prati y Dario Massabò. "Characterization of soot produced by the mini inverted soot generator with an atmospheric simulation chamber". Atmospheric Measurement Techniques 15, n.º 7 (8 de abril de 2022): 2159–75. http://dx.doi.org/10.5194/amt-15-2159-2022.
Kashdan, Julian. "Visualisation du mélange gazeux au sein de la chambre de combustion des moteurs par la fluorescence induite par laser". Photoniques, n.º 52 (marzo de 2011): 34–36. http://dx.doi.org/10.1051/photon/20115234.
FROMENT, Jean-Louis. "Moteurs Diesel : injection et chambre de combustion". Machines hydrauliques, aérodynamiques et thermiques, abril de 1999. http://dx.doi.org/10.51257/a-v1-bm2585.
FACCHINI, Bruno. "Refroidissement des turbines à gaz. Chambre de combustion". Machines hydrauliques, aérodynamiques et thermiques, julio de 2006. http://dx.doi.org/10.51257/a-v1-bm4567.
Bouam, Abdallah, Slimane Aissani y Rabah Kadi. "Amélioration des performances des turbines à gaz par injection de vapeur d’eau en amont de la chambre de combustion". Journal of Renewable Energies 11, n.º 2 (30 de junio de 2008). http://dx.doi.org/10.54966/jreen.v11i2.79.
Temmerman, Michaël, Ravo Andrianirina y Franck Richter. "Performances techniques et environnementales du four de carbonisation Green Mad Retort à Madagascar". BOIS & FORETS DES TROPIQUES 340 (15 de mayo de 2019). http://dx.doi.org/10.19182/bft2019.340.a31700.
Tesis sobre el tema "Chambre de combustion aéronautique":
Arroyo, Callejo Gustavo. "Modélisation thermique avancée d’une paroi multiperforée de chambre de combustion aéronautique avec dilution giratoire". Thesis, Toulouse, ISAE, 2016. http://www.theses.fr/2016ESAE0008/document.
Ln the combustion chamber, temperatures up to 2000K are reached, which exceeds by far the melting point of the liner materials. ln order to protect the liner, cool air from the combustion chamber outer casing is injected into the combustor through a large number of sub-millimeter closely-spaced holes (effusion cooling). However, strict environmental legislation has led jet-engine manufacturers to consider techniques that reduce the quantity of air available for cooling. Therefore, cooling system must be carefully designed. However, the size of the holes makes detailed numerical simulations unaffordable. Aerothermal models that mimic effusion cooling behavior are a promising solution. On the Other hand, up to now, far too little attention has been paid to a novel effusion cooling technique (compound angle effusion cooling), where cold air injection is not aligned With the hot air flow direction. The aim of this dissertation is twofold: to establish an effusion cooling model and to investigate the flow field of compound angle effusion cooling
Godel, Guillaume. "Modélisation de sous-maille de la combustion turbulente : développement d'outils pour la prédiction de la pollution dans une chambre aéronautique". Phd thesis, INSA de Rouen, 2010. http://tel.archives-ouvertes.fr/tel-00557904.
Hervo, Loïc. "Simulation numérique de l’écoulement d’un mélange air et phase dispersée pour l’allumage d’une chambre de combustion aéronautique via un formalisme Euler Lagrange". Thesis, Toulouse, ISAE, 2017. http://www.theses.fr/2017ESAE0043/document.
The goal of this thesis is to contribute to the development and validation of numerical tools for the Large Eddy Simulation (LES) of the ignition of a turbulent multiphase flow in a combustion chamber. An energy deposition method that models the energy supplied by the spark plug to the flow was implemented in the CEDRE code. This method was validated on a simulation of the ignition of a purely gaseous laminar propane-air flow. Then, a LES of the non-reacting gas flow in the monosector combustor MERCATO was performed with the Navier-Stokes solver CHARME of the CEDRE code. The comparison between simulations and experiments demonstrates that the main flow field features are well reproduced. In order to simulate the non-reacting dispersed two-phase flow of the same configuration, a simplified injection method called FIMUR was implemented in the Lagrangian solver SPARTE of the CEDRE code. In this method, droplets are injected directly at the tip of the injector with velocities deduced from experimental correlations while the size distribution is directly obtained from experimental data. The comparison of the mean droplet velocity and diameter fields in the vicinity of the injector between simulations and experiments appears satisfactory. Finally, LES's of the ignition of the MERCATO were performed using the non-reacting two-phase flow simulations and the aformentioned energy deposition method. Depending on the instant of energy deposition, the simulations lead to successful or failed ignitions. The flame propagation in a successful ignition was analysed in order to attempt to determine the physical phenomena at play and to better understand them
Burguburu, Joseph. "Etude expérimentale de la stabilité d'une flamme dans une chambre de combustion aéronautique par recirculation de gaz brûlés et par ajout d'hydrogène". Phd thesis, INSA de Rouen, 2012. http://tel.archives-ouvertes.fr/tel-00771860.
Burguburu, Joseph. "Etude expérimentale de la stabilité d’une flamme dans une chambre de combustion aéronautique par recirculation de gaz brûlés et par ajout d’hydrogène". Thesis, Rouen, INSA, 2012. http://www.theses.fr/2012ISAM0010/document.
Environmental standards on aircraff NOx emissions are strict. Technics for reducing them have drawbacks. Two options are explored in this study to supress them. The first one is to fundamentally change the current combustion chamber architecture, to stabilize them by a cavity, the second, to dope fuel at idle.Little information on the mechanisms of stabilization and on the flame structure on Trapped Vortex Combustor is available. To remedy this, a TVC is built. The stabilizing ans destabilizing parameters are pointed out by the cold flow investigation and the temporally resolved study of the combustion. The impact of the flame structure on pollutant emissions is also considered.The second part of this stud, deals with the addition of pure hydrogen an of reformer gas in a conventional combustuion chamber. Despite a slight increase in NOx emissions, the addition of hydrogenated compounds reduces drastically CO emissions, increases the flame stability and reduces the LBO limit
Royer, Alex. "Amélioration des méthodes de calcul thermique par réseau de neurones dans les chambres de combustion aéronautiques". Electronic Thesis or Diss., Université de Lorraine, 2023. http://www.theses.fr/2023LORR0141.
Aeronautical combustion chambers are constrained environments operating at temperatures and pressures that have been steadily increasing over the last decades. Under these conditions, radiative heat transfer is significant and its influence on flame structure and wall temperatures is noticeable. It is therefore essential to be able to accurately model this transfer mode on very heterogeneous industrial cases and on mesh of several hundred million cells. Common resolution methods do not provide satisfactory accuracy in view of the growing needs. A fine resolution and the use of spectral gas models would be necessary but would imply a prohibitive consumption of computing resources.To overcome this problem, we propose in this work a new radiation modelling methodology based on Monte Carlo methods and Bayesian neural networks. The principle of the concept detailed in this manuscript starts with the sampling of reference points randomly drawn in the study domain. The radiative quantity of interest is computed at each of these points using a Monte Carlo method and a fine spectral model. The results of these calculations are then stored in a database on which a neural network is trained using a Levenberg-Marquardt algorithm. The Bayesian paradigm allows us to define the optimal topology of the network and to automatically adapt the set of parameters inherent to the network without user intervention. The trained network allows to reconstitute the flux or flux divergence fields within the domain. After a theoretical description of the notions used in this work, results on academic cases are presented in different configurations. We then demonstrate the ability of the developed method to model radiation in a participatory environment with very high accuracy and low computational costs
Guignard, Olivier. "Vers une modélisation combinée des échanges thermiques conductifs, convectifs et radiatifs dans des chambres de combustion aéronautiques". Ecully, Ecole centrale de Lyon, 2005. http://bibli.ec-lyon.fr/exl-doc/oguignard.pdf.
The temperature levels reached in modern jet engines threaten the mechanical hold-up of confining walls. Air bleeding is necessary, which deteriorates the global aerothermal efficiency. In order to optimize it, designers use more and more elaborate numerical descriptions. In order to reproduce interactions between the various significant heat transfer modes, the corresponding simulation codes must exchange their outputs. However "coupling" type approaches remain very expensive from a computing point of view. "Chaining" type techniques could allow to approach the termal properties of the flow at a reduce cost. A methodology for the determination of the convection coefficient for cooling films is examined. Theoretical study and a practical application allow to underscore the conceptual error this methodology is suffering from. An alternative methodology is proposed to correct this error
Duchaine, Florent. "Optimisation de Forme Multi-Objectif sur Machines Parallèles avecMéta-Modèles et Coupleurs. Application aux Chambres de Combustion Aéronautiques". Phd thesis, Institut National Polytechnique de Toulouse - INPT, 2007. http://tel.archives-ouvertes.fr/tel-00362811.
Le but de ces travaux de thèse est de fournir une méthodologie basée sur des considérations issues de l'optimisation multi-objectif pour développer un outil de conception automatisé qui intègre des codes de simulation numérique pour évaluer les configurations. En premier lieu, les études concernent l'automatisation des procédures de simulation en insistant sur les aspects de génération automatique de maillage. Ensuite, le problème des temps de restitution liés à l'utilisation conjointe de techniques d'optimisation et de codes de calcul coûteux en ressources informatiques est adressé en proposant un algorithme basé sur des méta-modèles. L'outil final est construit à partir d'un coupleur de codes parallèles, lui conférant ainsi des caractéristiques intéressantes de performance et de flexibilité. Finalement, après divers tests de validation et d'évaluation, une application sur une chambre de combustion industrielle montre les capacités de la méthode à identifier des configurations prometteuses.
Dorey, Luc-Henry. "Modélisation des phénomènes couples combustion-formation des suies-transferts radiatifs dans les chambres de combustion de turbine à gaz". Phd thesis, Ecole Centrale Paris, 2012. http://tel.archives-ouvertes.fr/tel-00731144.
Dufitumukiza, Jean Pierre. "Développement des techniques optiques pour la caractérisation in-situ de la suie dans des foyers de combustion à haute pression". Electronic Thesis or Diss., Université de Lille (2022-....), 2023. https://pepite-depot.univ-lille.fr/ToutIDP/EDSMRE/2023/2023ULILR010.pdf.
The growth of air traffic urges combustion research to get a detailed understanding of the physical and chemical processes occurring in the aircraft engine; the main objectives are 1) to improve the combustion process and 2) to lower gaseous and particulate emissions. A solution to the first issue lies in the combustion at higher pressure and temperature, but this can impact the second issue, particularly concerning the production of soot and NOx emissions. To find a solution, it is necessary to develop experimental tools applied in representative combustion conditions relative to those encountered in aircraft engines in order to capture complex phenomena occurring inside these engines. To do this, a semi-industrial aeronautical test rig equipped with suitable optical diagnostics implemented/available at ONERA Palaiseau offers a glimpse of information into these combustion processes. As a result, this research aims to develop and implement optical techniques for characterizing soot particles in aeronautical engine-relevant combustors. Laser-Induced Incandescence (LII) is the primary technique on which efforts are directed. This technique is based on Planck's law radiation model. LII technique is used due to its high sensitivity for detecting the soot volume fraction and flexibility for its implementation in various optical configurations. In addition, the coupling of LII with other optical techniques presents a high interest in understanding the mechanisms and parameters leading to soot formation. First, Laser-Induced Fluorescence (LIF) is added as a complementary technique to detect soot precursors known as Polycyclic-Aromatic Hydrocarbons (PAHs). Secondly, light scattering provides information on the distribution of unburnt liquid fuel droplets and possible soot particle localization inside the combustor. Thirdly, OH* chemiluminescence illustrates the reaction zone and heat release. Finally, the PAHs and soot transportation or interactions with the flow field are tackled via particle image velocimetry (PIV)
Libros sobre el tema "Chambre de combustion aéronautique":
D, Roy G., ed. Advances in chemical propulsion: Science to technology. Boca Raton, FL: CRC Press, 2002.
Capítulos de libros sobre el tema "Chambre de combustion aéronautique":
Candel, Sébastien. "Chapitre 10 : La combustion et les défi s de la propulsion aéronautique et spatiale". En Chimie et transports, 175–94. EDP Sciences, 2020. http://dx.doi.org/10.1051/978-2-7598-1149-6-016.
Candel, Sébastien. "Chapitre 10 : La combustion et les défi s de la propulsion aéronautique et spatiale". En Chimie et transports, 175–94. EDP Sciences, 2020. http://dx.doi.org/10.1051/978-2-7598-1149-6.c016.