Thematische Bibliographien / Combustion chambre

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Auswahl der wissenschaftlichen Literatur zum Thema „Combustion chambre“

Autor: Grafiati

Veröffentlicht am 28. Juni 2021

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Zeitschriftenartikel zum Thema "Combustion chambre"

Serbin, Sergey. "THERMO ACOUSTIC PROCESSES IN LOW EMISSION COMBUSTION CHAMBER OF GAS TURBINE ENGINE CAPACITY 25 MW." Science Journal Innovation Technologies Transfer, no. 2019-2 (May 5, 2019): 86–90. http://dx.doi.org/10.36381/iamsti.2.2019.86-90.

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The appliance of modern tools of the computational fluid dynamics for the investigation of the pulsation processes in the combustion chamber caused by the design features of flame tubes and aerodynamic interaction compressor, combustor and turbine is discussed. The aim of the research is to investigate and forecast the non-stationary processes in the gas turbine combustion chambers. The results of the numerical experiments which were carried out using three-dimensional mathematical models in gaseous fuels combustion chambers reflect sufficiently the physical and chemical processes of the unsteady combustion and can be recommended to optimize the geometrical and operational parameters of the low-emission combustion chamber. The appliance of such mathematical models are reasonable for the development of new samples of combustors which operate at the lean air-fuel mixture as well as for the modernization of the existing chambers with the aim to develop the constructive measures aimed at reducing the probability of the occurrence of the pulsation combustion modes. Keywords: gas turbine engine, combustor, turbulent combustion, pulsation combustion, numerical methods, mathematical simulation.

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Léger, Bruno, Patrick André, Guy Grienche, and 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, no. 417 (1996): 625–30. http://dx.doi.org/10.1016/s0035-3159(96)80025-0.

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Kashdan, Julian. "Visualisation du mélange gazeux au sein de la chambre de combustion des moteurs par la fluorescence induite par laser." Photoniques, no. 52 (March 2011): 34–36. http://dx.doi.org/10.1051/photon/20115234.

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Łapinski, Damian, and Janusz Piechna. "Improvements in the turbo-engine by replacement of conventional combustion chamber by a pulse combustion chamber." Archive of Mechanical Engineering 60, no. 4 (2013): 481–94. http://dx.doi.org/10.2478/meceng-2013-0029.

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Abstract This paper comprises description of the turbo engine and evaluation of its analytical model. The analytical model was created to establish a benchmark for further evaluation of a wave rotor combustor (at constant volume). The wave rotor combustor concept was presented and discussed. Advantages of combustion at constant volume were described as well as the basic turbo engine updates required to reflect pulse combustor application. The calculation results for analytical model of a basic engine, and that equipped with pulse combustor are included in this paper. The paper describes the required changes in the engine structure and construction and the estimated thermodynamic improvements. Axial-type pulse multi-chamber combustion unit increasing the pressure and temperature of gases requires a special additional turbine utilizing additional energy and forming the interface between the standard compressor-turbine unit. Performance calculations done for an existing GTD-350 engine showed that constant-volume combustion process is valuable

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Arumugam, Sozhi, Pitchandi Kasivisvanathan, M. Arventh, and P. Maheshkumar. "Effect of Re-Entrant and Toroidal Combustion Chambers in a DICI Engine." Applied Mechanics and Materials 787 (August 2015): 722–26. http://dx.doi.org/10.4028/www.scientific.net/amm.787.722.

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This paper presents the experimental work to investigate the effect of Re-entrant and Toroidal combustion chambers in a DICI Engine. The two combustion chambers namely Re-entrant combustion chamber (RCC) and Toroidal combustion chamber (TCC) were fitted in a 4.4 kW single cylinder Direct Injection Compression Ignition (DICI) engine and tests were conducted with diesel. The influences of the combustion chamber geometry characteristics on combustion, performance and emissions characteristics have been investigated. This investigation shows the peak pressure of re-entrant chamber is higher than that of toroidal chamber. The heat release rate and brake thermal efficiency for re-entrant chamber are slightly higher than that of toroidal chamber. Specific fuel consumption is lower for toroidal chamber than that of re-entrant chamber. The enhancement in reduction of carbon monoxide, hydrocarbon is observed for Re-entrant chamber compared to the Toroidal chamber. Oxides of nitrogen are reduced for toroidal chamber than that of re-entrant chamber.

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Komarov, I. I., D. M. Kharlamova, A. N. Vegera та V. Y. Naumov. "Study on effect CO2 diluent on fuel cоmbustion in methane-oxygen combustion chambers". Vestnik IGEU, № 2 (30 квітня 2021): 14–22. http://dx.doi.org/10.17588/2072-2672.2021.2.014-022.

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Studying closed gas turbine cycles on supercritical carbon dioxide is currently a promising issue in the development of power energy sector in terms of increasing energy efficiency and minimizing greenhouse gas emissions into the atmosphere. Combustion of methane with oxygen in the combustion chamber occurs not in the nitrogen environment, but in the environment of carbon dioxide, that is the working fluid of the cycle, which is an inhibitor of chemical reactions. A large mass content of such a diluent of the reaction mixture in the volume of the chamber leads to the risks of significant chemical underburning, efficiency decrease of the combustion chamber and the cycle as a whole. The aim of the research is to study the kinetic parameters of the combustion of methane with oxygen in a supercritical CO2 diluent medium to ensure reliable and stable combustion of fuel by assessing the degree of the inhibitory effect of CO2 and determining its permissible amount in the active combustion zone of the combustion chamber. The research method is a numerical simulation of turbulent-kinetic processes of methane combustion in the combustion chamber using the reduced methane combustion mechanism. Ansys Fluent software package has been used. The authers have studied the impact of CO2 diluent on fuel cоmbustion in methane-oxygen combustion chambers. It is found that the combustor flame stabilization takes place if the content of СО2 diluent supplied to the mixture with oxidizer is 0,46–0,5 of mass fraction; additional СО2 diluent forms local low temperature zones which slow down the combustion process. When this happens, adding cooling СО2 into the flame stabilization zone should be eliminated. The study has found that no more than 20 % of the total carbon dioxide content should be supplied to the combustion chamber; to stabilize the flame and reduce its length, it is necessary to install blades to swirl the fuel and oxidizer mixed with CO2 at the inlet of the combustion chamber; CO2 supply for cooling should be carried out not less than 130 mm away from the burner mouth.

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Козел, Дмитрий Викторович. "Выбор геометрических характеристик фронтового устройства и длины камеры сгорания прямоточного типа". Aerospace technic and technology, № 4sup2 (27 серпня 2021): 19–28. http://dx.doi.org/10.32620/aktt.2021.4sup2.03.

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A method has been developed for selecting the geometric characteristics of the front and the length of the direct-flow combustion chamber. Afterburner combustion chambers are of the ramjet type and are used for a short-term increase in the thrust of a gas turbine engine during takeoff, for overcoming the sound barrier by an aircraft and for flying at supersonic speed, and for making maneuvers. As part of ramjet engines, ramjet combustion chambers are used as the main combustion chambers in which the process of fuel combustion and heat supply to the working fluid is ensured. The developed method for selecting the geometric characteristics consists in optimizing the main operating characteristics of the combustion chamber. Mathematical models are proposed for describing the dependence of the total pressure loss, the combustion efficiency and the range of stable operation of the combustion chamber against the parameters of the flow at the inlet to the combustion chamber and the geometric characteristics of the front device and the length of the combustion chamber. The analysis of the dependences of the combustion chamber working characteristics on the geometric characteristics of the front-line device and its length is carried out. As a result of the analysis of mathematical models, a list of the main geometric characteristics of the front device was determined, on which the total pressure loss, the combustion efficiency and the range of stable operation of the combustion chamber depend. Optimization parameters, optimization criterion and limits for solving the optimization problem are determined. As an implementation of the optimization method, it is proposed to use a diagram of the combustion chamber performance in the coordinates of the optimization parameters. The developed method makes it possible to ensure the optimal basic operating characteristics of the combustion chamber - total pressure loss, combustion efficiency and combustion stability limits.

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Pošta, J., B. Kadleček, and T. Hladík. "Engine combustion chamber tightness diagnostics." Research in Agricultural Engineering 49, No. 3 (2012): 115–18. http://dx.doi.org/10.17221/4961-rae.

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The modern combustion engines and their systems are getting more complicated and sophisticated nowadays. It is no more possible to verify their function or actual technical state directly. Thus various methods of indirect diagnostics are being developed more and more rapidly. The on-board diagnostics is being increasingly applied to monitor and measure suitable diagnostic signals during operation, deviations from required or expected values are then recorded. This trend requires the application of completely disassembly-free techniques of measurements and the real-time analyzing of measured figures. This paper presents the results of the research on relation between the starter&rsquo;s starting current and the engine combustion chamber tightness. The experiments were carried out for common four-cylinder engine.

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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 (convergent, divergent, convergent-divergent and divergent-convergent combustion chamber). Premixed mixture of hydrogen-air has been used as reactants for the current investigation. Turbulence model implemented in this paper is RNG k-epsilon and combustion reaction was modeled with 10 species and 21 steps scheme using Eddy Dissipation Concept model. Two non-dimensional numbers d1/d2 (inlet to outlet diameter ratio) and d1/d3 (inlet to throat diameter ratio) are defined. For d1/d2 > 1.0, the combustion chamber is convergent, otherwise it is divergent. When d1/d3 > 1.0, the micro combustor is convergent-divergent and for d1/d3 < 1.0, the micro combustor is divergent-convergent. The results indicate that with increasing d1/d2, the liftoff occurs in a lower inlet flow velocity. With varying d1/d3, from 0.71 (2.0/2.8) to 1.0 (2.0/2.0), the liftoff velocity is reduced. Based on the numerical results, it can be said that the use of convergent and convergent-divergent combustion chamber decreases liftoff velocity. Meanwhile, the combustor with diverging and diverging-converging structure can enhance liftoff velocity. In the same condition, critical liftoff velocity of divergent-convergent micro combustor is the highest among all cases and this configuration is appropriate for Micro Electro-Mechanical Systems that work with high inlet velocity.

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Shang, Yong, Fu Shui Liu, Xiang Rong Li, and Jing Wu. "Research on Parametric Design Method of Combustion Chamber on Diesel Engine." Advanced Materials Research 383-390 (November 2011): 1431–40. http://dx.doi.org/10.4028/www.scientific.net/amr.383-390.1431.

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One method of parametric design on combustion chamber is used in this paper. Several independent geometrical parameters of ω type and double swirl combustion chamber are brought forward. Different series of ω type and double swirl combustion chambers have been designed by using this method. The effect of the independent geometrical parameters on the performance of diesel engine has been studied by using CFD code AVL FIRE. According to this method of parametric design and calculation result, two pistons with ω type and double swirl combustion chamber has been designed with the target of the highest indicated heat efficiency. The test result shows that, contrasting with ω type chamber, BSFC and main combustion duration of double swirl combustion chamber is lower by 7.5 and 6.9 percent respectively, while indicated heat efficiency is 7.1 percent higher. And the calculation result has coherence with the experiment. It is proved that the method of parametric design on combustion chamber can satisfy the requirement of designing. At the same time, this method can be extended to design other combustion chambers.

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Dissertationen zum Thema "Combustion chambre"

Philip, Maxime. "Dynamique de l’allumage circulaire dans les foyers annulaires multi-injecteurs." Thesis, Université Paris-Saclay (ComUE), 2016. http://www.theses.fr/2016SACLC034/document.

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L’allumage constitue une phase critique dans de nombreuses applications de combustion et plus particulièrement dans celles qui sont liées à la propulsion aéronautique et spatiale. Un des défis actuels a été de développer des simulations aux grandes échelles de ce phénomène transitoire dans des configurations réalistes comme celles trouvées dans les moteurs aéronautiques. A cet égard, le travail pionnier de Boileau et al. (2008)a indiqué que des calculs complets de ce processus pouvaient être réalisés dans des géométries complètes de chambre de combustion annulaire et que ces calculs pouvaient fournir des informations de première main sur le processus d’allumage circulaire. Il était toutefois important devoir si la simulation pouvait reproduiredes données expérimentales bien contrôlées.Ceci est accompli dans le présent travail qui utilise un dispositif expérimental nouveau désigné sous le nom de MICCA.La thèse décrit l’ensemble des données recueillies au cours d’essais systématiques sur MICCA, la méthode de calcul aux grandes échelles et sa validation dans une configuration de brûleur simplifiée, les résultats de simulations aux grandes échelles du processus d’allumage circulaire, une analyse détaillée des résultats numériques et enfin une modélisation simplifiée du processus d’allumage fondée sur des équations de bilan macroscopiques Ignition constitutes a critical phase in many combustion applications and specifically those related to aerospace propulsion. One of the current challenges has been to develop large eddy simulations of this transient phenomenon in realistic configurations like those found in aeroengines.In this respect, the pioneering work of Boileau et a. (2008) indicated that complete calculations of this process in a full annular combustor geometry could be carried out and that they provided first hand information on the light-round process.It was however important to see if the simulation can match well controlled experimental data. This is accomplished in the present work which uses a novel experimental device named MICCA. The thesis describes the experimental set of data,the calculation methodology and its validation in a single burner configuration,results of large eddy simulation of the full light round process, a detailed analysis of the numerical results and an attempt to build a simplified model of the process based on macroscopic balance equations

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Prieur, Kevin. "Dynamique de la combustion dans un foyer annulaire multi-injecteurs diphasique." Thesis, Université Paris-Saclay (ComUE), 2017. http://www.theses.fr/2017SACLC070/document.

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Ces dernières décennies ont vu apparaître de nombreuses innovations dans le domaine de la combustion afin de réduire la consommation et les émissions polluantes. De nouveaux types d'injecteur, de type LPP - Lean Premixed Prevaporized, ont été mis au point permettant de diminuer le rapport combustible/air et visent à pré-vaporiser le carburant en amont de la combustion afin de mieux le mélanger à l'air issu du compresseur. Cette architecture permet une amélioration de la consommation et des émissions polluantes, mais rend les foyers annulaires plus sensibles à des phénomènes instationnaires qui perturbent le fonctionnement du système, accroissent les flux de chaleur vers les parois de la chambre, induisent des vibrations de structures, entrainent une fatigue cyclique des pièces mécaniques et dans des cas extrêmes conduisent à des dommages irréversibles. L'objectif est de poursuivre l'effort engagé au laboratoire EM2C sur ce thème et plus particulièrement sur celui de la dynamique de la combustion dans les chambres annulaires. La thèse concerne plus spécialement le cas où l'injection du combustible s'effectue sous forme liquide. La configuration reproduit sous forme idéalisée celle que l'on trouve en pratique dans les moteurs aéronautiques. La chambre, désignée sous le nom de MICCA-Spray, est équipée de 16 injecteurs swirlés pouvant être alimentés par un combustible liquide ou gazeux, permettant ainsi une combustion diphasique ou prémélangée. Le système possède des parois en quartz donnant un accès optique à la zone de flamme. Il est aussi équipé d'un ensemble de diagnostics tels des microphones, des photomultiplicateurs ainsi que des systèmes d'imagerie à haute cadence These last decades have seen many innovations in the field of combustion to reduce fuel consumption and pollutant emissions. New types of injector, for example LPP - Lean Premixed Prevaporized, have then been developed to reduce the fuel / air ratio and aim to pre-vaporize the fuel upstream of the combustion in order to mix it better with the air coming from the compressor. Unfortunately this architecture makes annular chambers more sensitive to unsteady phenomena which disturb the functioning of the system, increase the heat flows towards the walls of the chamber, induce vibrations of structures, cause cyclic fatigue of mechanical parts and in extreme cases lead to irreversible damage. The objective of this thesis is to continue the effort undertaken at the EM2C laboratory on this topic and more particularly on the dynamics of combustion in annular chambers comprising a set of injectors. The thesis concerns more particularly the case where the injection of the fuel takes place in liquid form. This configuration reproduces, in idealized form, what can be found in practice in aeronautical engines. It is also a configuration studied at the fundamental level. The chamber, known as MICCA-Spray, is equipped with 16 swirled injectors that can be powered by liquid or gaseous fuel, thus enabling two-phase or fully premixed combustion. The system has quartz walls giving optical access to the flame zone. It is also equipped with a set of diagnostics such as microphones, photomultipliers and high-speed imaging systems

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Cuif, Sjöstrand Marianne. "Simulations Numériques Directes d’une méso-chambre de combustion : Mise en oeuvre et analyses." Thesis, Rouen, INSA, 2012. http://www.theses.fr/2012ISAM0022/document.

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La méso-combustion est le régime de combustion où la taille caractéristique du domaine est juste supérieure à la distance de coincement de la flamme , typiquement de l'ordre du centimètre. La difficile réalisation de systèmes de combustion fonctionnant en ce régime de flamme particulier suscite l'intérêt : il devient alors possible de tirer parti de la haute densité énergétique des hydrocarbures pour concevoir des systèmes de production d'énergie plus compacts. Nous nous intéressons à la réalisation de calculs DNS compressibles d'une chambre de combustion cubique de 8 x 10 x 8 mm3. Ce travail présente autant la mise en œuvre des calcules, en particulier la problématique de la condition frontière mur, que les résultats obtenus. Ces derniers nous permettent d'analyser la phénoménologie complexe de cet écoulement réactif confiné et serviront de base à des modélisations futures Meso-combustion can be defined as the combustion regime where the involved lenghts scales are close but slightly larger than the quenching distance of the flame, tipically smaller than a cm. By taking advantage of the high energetic density of liquid hydrocarbons, it would become possible to build small-sized combustion-based long-lived lighter electrical power systems. However combsution phenomena at these meso-scales have their own shortcomings. Indeed, by decreasing the system size, the usual phenomenological balance betwenne chemical reactions, mixing, turbulence and heat transfer is changed. In the present work, we focus on the DNS calculation of a cubic meso-combsution chamber of 8 x 10 x 8 mm3. This works presents the implementation of the numerical strategy used, with a specific attention to the no-slip wall compressible boundary condition. We then present an analysis of this particular reactive flow. The results are useful for future modeling of such a combustor

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Moreau, Denis. "Etude de mélange de jets gazeux dans une chambre de combustion." Grenoble 2 : ANRT, 1988. http://catalogue.bnf.fr/ark:/12148/cb37616639q.

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Moreau, Denis. "Etude de mélange de jets gazeux dans une chambre de combustion." Rouen, 1988. http://www.theses.fr/1988ROUES043.

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Etude expérimentale du mélange de plusieurs jets ronds gazeux dans différents types de configuration (doublet, triplet, quintriplet, multitriplet). Emploi de deux méthodes de diagnostic: visualisation par tomographie flash (étude qualitative de la structure des jets avant et après l'interaction) et méthode thermique (évolution du mélange par la mesure des caractéristiques du champ de température)

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Kechabia, Rachid Alexandre. "Etude experimentale et numerique d'une chambre de combustion de laser chimique." Paris 6, 1992. http://www.theses.fr/1992PA066195.

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Des instabilites basse frequence perturbent le fonctionnement des lasers chimiques ayant probablement leur origine dans la chambre de combustion. Il a donc ete decide d'entreprendre une etude detaillee, a la fois numerique et experimentale, de l'ecoulement dans une telle chambre. Dans le premier chapitre on etudie experimentalement les phenomenes de melange et d'interaction de jets issus de divers types d'injecteurs. Un certain nombre de visualisations par tomographie laser et de phenomenes originaux sont montres. L'interet de cette partie reside dans la possibilite de mieux definir a la fois les criteres de choix entre divers types d'injections et les conditions optimales de fonctionnement. Le second chapitre est consacre a l'etude aerodynamique d'un ecoulement dans une chambre parallelepipedique simulant la chambre de combustion. Un code de calcul est developpe pour resoudre les equations de navier-stokes incompressible. Puis une confrontation calcul-experience est presentee. Le troisieme chapitre est consacre a l'etude aerothermique de l'ecoulement resultant de l'injection d'air chaud dans la chambre. L'hypothese de boussinesq concernant la variation de masse volumique est retenue. Les coefficients thermodynamiques du fluide sont pris constants. Une equation supplementaire d'energie est utilisee pour le developpement du nouveau code thermique. La temperature est mesuree experimentalement. Une confrontation calcul-experience est presentee ici aussi

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Courtois, Raphaël. "Simulation aux grandes échelles de l'écoulement dans un chambre de combustion en forme de marche descendante." Châtenay-Malabry, Ecole centrale de Paris, 2005. http://www.theses.fr/2005ECAP1004.

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Cette thèse est consacrée à la simulation aux grandes échelles (SGE) de l’écoulement dans une chambre de combustion en forme de marche descendante. Cette technique de simulation rend possible l’étude des phénomènes instationnaires et permet en particulier d’analyses le couplage entre la dynamique du front de flamme et l’écoulement. Dans le cadre de cette thèse, la chambre d’expérimentale en forme de marche descendante appelée chambre A3C a été choisie comme cas test. Cette chambre a en effet été l’objet, au laboratoire LAERTE de l’ONERA, de nombreuses mesures qui ont permis d’établir une base de données expérimentales fournie en champs moyens de température et de vitesse. Ces résultats expérimentaux servent de référence pour les calculs numériques effectués au cours de cette thèse. Les phénomènes instationnaires mis en évidence dans les calculs font aussi l’objet d’une analyse. Le code de calcul utilisé est le code AVBP développé au CERFACS. Dans un premier temps, notre étude a porté sur le cas simplifié de l’écoulement non réactif. Des calculs bidimensionnels ont d’abord été réalisés dans le cadre d’une prise en main du code AVBP. Une série de tests a ensuite été menée de façon à valider le code dans le cas de calculs tridimensionnels, plus réalistes. Dans un second temps, la combustion a été prise en compte grâce à un modèle de flamme épaissie. Une série de calculs bidimensionnels a d’abord été menée afin d’évaluer la fiabilité de test de calculs. Des calculs tridimensionnels ont ensuite été réalisés de façon à prendre totalement en compte l’influence de la turbulence sur le front de flamme. Ces calculs tridimensionnels sont très coûteux et leur intérêt est donc discuté The large Eddy Simulation (LES) has been used ti simulate the flow in a backward facing step combustor. The LES allows to investigate the unsteady phenomena and, in particular, the interaction of the flame with the flow. The use of LES for reacting flows is recent because is started in the middle of ninety’s. For that reason many validation studies continue to be undertaken. In this thesis, the experimental backward facing step chamber, named A3C, has been chosen. Many measurements have been carried out in the LAERTE (ONERA) and have given rise to important data basis in mean temperature (DRASC) and mean velocity (LDV). These results are compared with our LES simulations. The unsteady phenomena appearing in the simulations are also analysed. The AVBP code developed by the CERFACS has been used for these simulations. Initially, our study concerned the simplified case of non reactive flow. Twodimensional simulations have been first carried out to learn the use and the behaviour of the AVBP code. Then, more realistic tridimensional calculations have been carried out in order to validate the code. In a second time, the combustion has been introduced by the means of the thiskened flame model. Twodimensional simulations have been first undertaken in order to evaluate the reliability of such calculations. Then, tridimensional simulations have been achieved in order to take into account the influence of the tridimensional turbulence in front flame. These tridimensional simulationshave a very high coast and their interest is discussed

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Alizon, Franck Pascal. "Transferts de chaleur convectifs dans la chambre de combustion des moteurs à combustion interne : Influence de l'aérodynamique interne." Paris 6, 2005. http://www.theses.fr/2005PA066116.

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Erchiqui, Fouad. "Modelisation mathematique d'une chambre de combustion par la methode des plans imaginaires." Thèse, Chicoutimi : Université du Québec à Chicoutimi, 1987. http://theses.uqac.ca.

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Memoire (Sc. A.) --Universite du Quebec a Chicoutimi, 1987. En tete du titre: Memoire presente a l'Universite du Queec a Chicoutimi comme exigence partielle pour l'obtention du grade de maitre es sciences appliquees. CaQCU Bibliogr.: ff. 60-61. Document électronique également accessible en format PDF. CaQCU

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Fortier-Topping, Hugo. "Conception d'une chambre de combustion pour la microturbine à gaz SRGT-2." Mémoire, Université de Sherbrooke, 2014. http://hdl.handle.net/11143/5417.

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Dans un contexte mondial où les ressources énergétiques commencent à se faire rares, beaucoup de recherches se font sur l’amélioration de l’efficacité thermique et de la densité de puissance des sources d’énergie existantes. Ainsi, un projet de développement d’une microturbine à gaz avec une architecture de nouveau genre permettant d’augmenter la densité de puissance tout en réduisant les coûts a vu le jour. La recherche proposée dans le présent document se concentre sur la conception et la caractérisation d’une chambre de combustion et d’un banc d’essai pour la turbine SRGT-2. Une chambre de combustion à écoulement inverse est conçue et caractérisée expérimentalement. Un modèle 0D de la chambre est tout d’abord fait. Par la suite, une optimisation numérique est faite jusqu’à l’atteinte des objectifs de conception. Finalement, la chambre de combustion est testée durant 30 secondes avec de l’hydrogène comme carburant. Une température de sortie de la chambre de combustion de 1000 K a été maintenue avec une efficacité de combustion de plus de 85%. Le banc d’essai conçu pour le projet de recherche utilise un démarreur électropneumatique permettant d’accélérer le prototype jusqu’à 102 000 RPM. Le module fluide est la partie du banc d’essai qui contient les différentes parties de la turbine SRGT-2 comme le rotor, les stators et la chambre de combustion. Le module est instrumenté dans le but d’obtenir une caractérisation complète de la turbine. Sa configuration modulaire permet aussi de caractériser chacune des composantes individuellement en changeant certaines sections.

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Bücher zum Thema "Combustion chambre"

Combustion system design. PennWell Books, 1996.

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Moon, H. J. Soot generation in a diesel combustion chamber. UMIST, 1996.

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Quentmeyer, Richard J. Rocket combustion chamber life-enhancing design concepts. National Aeronautics and Space Administration, Lewis Research Center, 1990.

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Grigorʹev, A. V. Teorii︠a︡ kamery sgoranii︠a︡. Nauka, 2010.

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Shyy, W. A numerical study of flow in gas-turbine combustor. AIAA, 1987.

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Tamaru, Takashi. Hydrogen fueled subsonic-ram-combustor model tests for an air-turbo-ram engine. National Aerospace Laboratory, 1990.

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Hu, Tin Cheung John. An experimental and computational investigation of an annular reverse-flow combustor. University of Toronto, 1991.

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Colannino, Joseph. Modeling of combustion systems: A practical approach. CRC/Taylor & Francis, 2006.

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Gafurov, R. A. Diagnostika vnutrikamernykh prot͡s︡essov v ėnergeticheskikh ustanovkakh. "Mashinostroenie", 1991.

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Jacobs, P. A. Flow establishment in a generic scramjet combustor. Institute for Computer Applications in Science and Engineering, 1990.

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Buchteile zum Thema "Combustion chambre"

Seitz, Timo, Ansgar Lechtenberg, and Peter Gerlinger. "Rocket Combustion Chamber Simulations Using High-Order Methods." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_24.

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Abstract High-order spatial discretizations significantly improve the accuracy of flow simulations. In this work, a multi-dimensional limiting process with low diffusion (MLP$$^\text {ld}$$) and up to fifth order accuracy is employed. The advantage of MLP is that all surrounding volumes of a specific volume may be used to obtain cell interface values. This prevents oscillations at oblique discontinuities and improves convergence. This numerical scheme is utilized to investigate three different rocket combustors, namely a seven injector methane/oxygen combustion chamber, the widely simulated PennState preburner combustor and a single injector chamber called BKC, where pressure oscillations are important.

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El Hefni, Baligh, and Daniel Bouskela. "Combustion Chamber Modeling." In Modeling and Simulation of Thermal Power Plants with ThermoSysPro. Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-05105-1_8.

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Armbruster, Wolfgang, Justin S. Hardi, and Michael Oschwald. "Experimental Investigation of Injection-Coupled High-Frequency Combustion Instabilities." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_16.

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Abstract Self-excited high-frequency combustion instabilities were investigated in a 42-injector cryogenic rocket combustor under representative conditions. In previous research it was found that the instabilities are connected to acoustic resonance of the shear-coaxial injectors. In order to gain a better understanding of the flame dynamics during instabilities, an optical access window was realised in the research combustor. This allowed 2D visualisation of supercritical flame response to acoustics under conditions similar to those found in European launcher engines. Through the window, high-speed imaging of the flame was conducted. Dynamic Mode Decomposition was applied to analyse the flame dynamics at specific frequencies, and was able to isolate the flame response to injector or combustion chamber acoustic modes. The flame response at the eigenfrequencies of the oxygen injectors showed symmetric and longitudinal wave-like structures on the dense oxygen core. With the gained understanding of the BKD coupling mechanism it was possible to derive LOX injector geometry changes in order to reduce the risks of injection-coupled instabilities for future cryogenic rocket engines.

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Haidn, Oskar J., Nikolaus A. Adams, Rolf Radespiel, et al. "Collaborative Research for Future Space Transportation Systems." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_1.

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Abstract This chapter book summarizes the major achievements of the five topical focus areas, Structural Cooling, Aft-Body Flows, Combustion Chamber, Thrust Nozzle, and Thrust-Chamber Assembly of the Collaborative Research Center (Sonderforschungsbereich) Transregio 40. Obviously, only sample highlights of each of the more than twenty individual projects can be given here and thus the interested reader is invited to read their reports which again are only a summary of the entire achievements and much more information can be found in the referenced publications. The structural cooling focus area included results from experimental as well as numerical research on transpiration cooling of thrust chamber structures as well as film cooling supersonic nozzles. The topics of the aft-body flow group reached from studies of classical flow separation to interaction of rocket plumes with nozzle structures for sub-, trans-, and supersonic conditions both experimentally and numerically. Combustion instabilities, boundary layer heat transfer, injection, mixing and combustion under real gas conditions and in particular the investigation of the impact of trans-critical conditions on propellant jet disintegration and the behavior under trans-critical conditions were the subjects dealt with in the combustion chamber focus area. The thrust nozzle group worked on thermal barrier coatings and life prediction methods, investigated cooling channel flows and paid special attention to the clarification and description of fluid-structure-interaction phenomena I nozzle flows. The main emphasis of the focal area thrust-chamber assembly was combustion and heat transfer investigated in various model combustors, on dual-bell nozzle phenomena and on the definition and design of three demonstrations for which the individual projects have contributed according to their research field.

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Olmeda, R., P. Breda, C. Stemmer, and M. Pfitzner. "Large-Eddy Simulations for the Wall Heat Flux Prediction of a Film-Cooled Single-Element Combustion Chamber." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_14.

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Abstract In order for modern launcher engines to work at their optimum, film cooling can be used to preserve the structural integrity of the combustion chamber. The analysis of this cooling system by means of CFD is complex due to the extreme physical conditions and effects like turbulent fluctuations damping and recombination processes in the boundary layer which locally change the transport properties of the fluid. The combustion phenomena are modeled by means of Flamelet tables taking into account the enthalpy loss in the proximity of the chamber walls. In this work, Large-Eddy Simulations of a single-element combustion chamber experimentally investigated at the Technical University of Munich are carried out at cooled and non-cooled conditions. Compared with the experiment, the LES shows improved results with respect to RANS simulations published. The influence of wall roughness on the wall heat flux is also studied, as it plays an important role for the lifespan of a rocket engine combustors.

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Pfeifer, Christian, Jonas P. Moeck, C. Oliver Paschereit, and Lars Enghardt. "Localization of Sound Sources in Combustion Chambers." In Combustion Noise. Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-642-02038-4_10.

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Fiedler, Torben, Joachim Rösler, Martin Bäker, et al. "Mechanical Integrity of Thermal Barrier Coatings: Coating Development and Micromechanics." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_19.

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Abstract To protect the copper liners of liquid-fuel rocket combustion chambers, a thermal barrier coating can be applied. Previously, a new metallic coating system was developed, consisting of a NiCuCrAl bond-coat and a Rene 80 top-coat, applied with high velocity oxyfuel spray (HVOF). The coatings are tested in laser cycling experiments to develop a detailed failure model, and critical loads for coating failure were defined. In this work, a coating system is designed for a generic engine to demonstrate the benefits of TBCs in rocket engines, and the mechanical loads and possible coating failure are analysed. Finally, the coatings are tested in a hypersonic wind tunnel with surface temperatures of 1350 K and above, where no coating failure was observed. Furthermore, cyclic experiments with a subscale combustion chamber were carried out. With a diffusion heat treatment, no large-scale coating delamination was observed, but the coating cracked vertically due to large cooling-induced stresses. These cracks are inevitable in rocket engines due to the very large thermal-strain differences between hot coating and cooled substrate. It is supposed that the cracks can be tolerated in rocket-engine application.

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Hötte, Felix, Oliver Günther, Christoph von Sethe, Matthias Haupt, Peter Scholz, and Michael Rohdenburg. "Lifetime Experiments of Regeneratively Cooled Rocket Combustion Chambers and PIV Measurements in a High Aspect Ratio Cooling Duct." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_18.

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Abstract This paper aims at experimental investigations of the life limiting mechanisms of regeneratively cooled rocket combustion chambers, especially the so called doghouse effect. In this paper the set up of a cyclic thermo-mechanical fatigue experiment and its results are shown. This experiment has an actively cooled fatigue specimen that is mounted downstream of a subscale GOX-GCH$$_{\text {4}}$$ combustion chamber with rectangular cross section. The specimen is loaded cyclically and inspected after each cycle. The effects of roughness, the use of thermal barrier coatings, the length of the hot gas phase, the oxygen/fuel ratio and the hot gas pressure are shown. In a second experiment the flow in a generic high aspect ratio cooling duct is measured with the Particle Image Velocimetry (PIV) to characterize the basic flow. The main focus of the analysis is on the different recording and processing parameters of the PIV method. Based on this analysis a laser pulse interval and the window size for auto correlation is chosen. Also the repeatability of the measurements is demonstrated. These results are the starting point for future measurements on the roughness effect on heat transfer and pressure loss in a high aspect ratio cooling duct.

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Richter, Christoph, Łukasz Panek, Verina Krause, and Frank Thiele. "Investigations Regarding the Simulation of Wall Noise Interaction and Noise Propagation in Swirled Combustion Chamber Flows." In Combustion Noise. Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-642-02038-4_8.

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Bake, Friedrich, André Fischer, Nancy Kings, and Ingo Röhle. "Investigation of the Correlation of Entropy Waves and Acoustic Emission in Combustion Chambers." In Combustion Noise. Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-642-02038-4_5.

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Konferenzberichte zum Thema "Combustion chambre"

Sakurai, Takashi, and Shunsuke Nakamura. "Performance and Operating Characteristics of Micro Gas Turbine Driven by Pulse, Pressure Gain Combustor." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-15000.

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Abstract This paper presents the experimental results of a micro gas turbine driven by pulse, pressure gain combustor. The aim of this study is to demonstrate the improvement of the engine performance by applying the pressure gain combustion. The micro gas turbine is composed of a combustor having two combustion chambers and an automotive turbocharger which is used as a compressor and a turbine. The outlets of two combustion chambers are joined by a confluence part to connect with the turbine. By changing the combustion methods of each combustion chamber, the gas turbine was operated in three modes; normal combustion mode, pulse combustion augmented mode, and fully pulse combustion mode. In the normal combustion mode, two combustion chambers were operated under continuous, constant-pressure combustion. In the pulse combustion augmented mode, one combustion chamber was operated under continuous, constant-pressure combustion and the other was operated under pulse combustion. In the fully pulse combustion mode, two combustion chambers were operated under pulse combustion. The pulse combustion applied in this study was the forced-ignition type, active pulse combustion. Although the pressure increase was attained by the pulse combustion comparing with the normal combustion, the mass-averaged pressure in the combustor showed that the net pressure gain in the combustor was not attained. The engine performance such as thermal efficiency and work and operating characteristics of gas turbine were investigated for two operation modes. In the pulse combustion augmented mode, the gas turbine could successfully sustain its operation as well as normal operation mode. The increase in the combustor pressure affected the air mass flow rate and the compressor performance, resulted in the decrease of performance comparing with the normal combustion mode.

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Tamaru, T., K. Shimodaira, Y. Kurosawa, and T. Kuyama. "Combustion Instability of a Gas Turbine Combustor up to 50-Atmosphere Condition." In ASME 1986 International Gas Turbine Conference and Exhibit. American Society of Mechanical Engineers, 1986. http://dx.doi.org/10.1115/86-gt-175.

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Combustion instabilities or blow-off phenomena at high pressure conditions were investigated on practical can-type combustion chambers. An air loading parameter, ma/VP2 at constant inlet temperature, was used to evaluate the allowable air flow rate in the combustion chamber. It was found that the pressure dependency of the parameter was not adequate for the high pressure conditions. It is revealed that the blow-off velocity in the flame holding region is related to the maximum laminar burning velocity corresponding to the pressure and temperature and that the velocity in the primary zone must be a very small value at high pressure condition.

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Tsuji, Yoshifumi, Bennett Sprague, David Walther, Albert Pisano, Carlos Fernandez-Pello, and Carlos Fernandez-Pello. "Effect of Chamber Width on Flame Characteristics in Small Combustion Chambers." In 43rd AIAA Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-943.

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Vítek, Oldřich, Jan Macek, and Miloš Polášek. "Simulation of Pre-Chambers in an Engine Combustion Chamber Using Available Software." In SAE 2003 World Congress & Exhibition. SAE International, 2003. http://dx.doi.org/10.4271/2003-01-0373.

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Liu, Chengke, and G. A. Karim. "3D-CFD Simulation of Diesel and Dual Fuel Engine Combustion." In ASME 2007 Internal Combustion Engine Division Fall Technical Conference. ASMEDC, 2007. http://dx.doi.org/10.1115/icef2007-1621.

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A 3D-CFD model with a reduced detailed chemical kinetics of the combustion of diesel and methane fuels is developed while considering turbulence during combustion to simulate the mixture flow, formation and combustion processes within diesel and diesel/methane dual fuel engines having swirl chambers. The combustion characteristics of the pilot injection into a small pre-chamber are also investigated and compared with those within a swirl chamber. Modeling results were validated by a group of corresponding experimental data. The spatial and temporal distributions of the mixture temperature, pressure and velocity under conditions with and without liquid fuel injection and combustion are compared in the swirl and main combustion chambers. The effects of engine speed, injection timing, and the addition of carbon dioxide on the combustion process of dual fuel engines are investigated. It is found that in the absence of any fuel injection and combustion, the swirl center is initially formed at the bottom left of the swirl chamber, and then moved up with continued compression in the top-right direction toward the highest point. The swirling motion within the swirl and main combustion chambers promotes the evaporation of the liquid pilot and the combustion processes of diesel and dual fuel engines. It was observed that an earlier autoignition can be obtained through injecting the pilot fuel into the small prechamber compared to the corresponding swirl chamber operation. It is to be shown that reduced engine emissions and improved thermal efficiency can be achieved by two-stage HCCI combustion.

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Hessel, Randy P., Ettore Musu, Salvador M. Aceves, and Daniel L. Flowers. "A General Rezoning Technique for KIVA3V Internal Combustion Engines CFD Simulations." In ASME 2010 Internal Combustion Engine Division Fall Technical Conference. ASMEDC, 2010. http://dx.doi.org/10.1115/icef2010-35147.

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A computational mesh is required when performing CFD-combustion modeling of internal combustion engines. For combustion chambers with moving pistons and valves, like those in typical cars and trucks, the combustion chamber shape changes continually in response to piston and valve motion. The combustion chamber mesh must then also change at each time step to reflect that change in geometry. The method of changing the mesh from one computational time step to the next is called rezoning. This paper introduces a new method of mesh rezoning for the KIVA3V CFD-combustion program. The standard KIVA3V code from Los Alamos National Laboratory comes with standard rezoners that very nicely handle mesh motion for combustion chambers whose mesh does not include valves and for those with flat heads employing vertical valves. For pent-roof and wedge-roof designs KIVA3V offers three rezoners to choose from, the choice depending on how similar a combustion chamber is to the sample combustion chambers that come with KIVA3V. Often, the rezoners must be modified for meshes of new combustion chamber geometries to allow the mesh to successfully capture change in geometry during the full engine cycle without errors. There is no formal way to approach these modifications; typically this requires a long trial and error process to get a mesh to work for a full engine cycle. The benefit of the new rezoner is that it replaces the three existing rezoners for canted valve configurations with a single rezoner and has much greater stability, so the need for ad hoc modifications of the rezoner is greatly reduced. This paper explains how the new rezoner works and gives examples of its use.

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Kalghatgi, G. T., and R. J. Price. "Combustion Chamber Deposit Flaking." In International Fuels & Lubricants Meeting & Exposition. SAE International, 2000. http://dx.doi.org/10.4271/2000-01-2858.

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de Boer, C. D., and D. W. Grigg. "Gasoline Engine Combustion — The Nebula Combustion Chamber." In 22nd FISITA Congress. SAE International, 1988. http://dx.doi.org/10.4271/885148.

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Schwalb, James A., and Thomas W. Ryan. "Emissions Measurements in a Steady Combusting Spray Simulating the Diesel Combustion Chamber." In International Congress & Exposition. SAE International, 1992. http://dx.doi.org/10.4271/920185.

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Aghakashi, V., M. H. Saidi, A. Ghafourian, and A. A. Mozafari. "Analysis of Temperature Distribution Over a Gas Turbine Shaft Exposed to a Swirl Combustor Flue." In 2010 14th International Heat Transfer Conference. ASMEDC, 2010. http://dx.doi.org/10.1115/ihtc14-22628.

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Gas turbine shaft is generally exposed to high temperature gases and may seriously be affected and overheated due to temperature fluctuations in the combustion chamber. Considering vortex flow in the combustion chamber, it may increase the heat release rate and combustion efficiency and also control location of energy release. However, this may result in excess temperature on the combustor equipments and gas turbine shaft. Vortex flow in the vortex engine which is created by the geometry of combustion chamber and conditions of flow field is a bidirectional swirl flow that maintains the chamber wall cool. In this study a new gas turbine combustion chamber implementing a liner around the shaft and liquid fuel feeding system is designed and fabricated. Influence of parameters such as axial position in the combustor direction and equivalence ratio are studied. Experimental results are compared with the numerical simulation by the existing commercial software. Swirl number i.e. ratio of angular flux of angular momentum to angular flux of linear momentum multiplied by nozzle radius, in this study is assumed to be constant. In order to measure the temperature along the liner, K type thermocouples are used. Results show that the heat transfer to the liner at the inlet of combustion chamber is enough high and at the outlet of combustion chamber is relatively low. The effect of parameters such as equivalence ratio and the mass flow rate of oxidizer on the temperature of the liner is investigated and compared with the numerical solution. This type of combustion chambers can be used in gas turbine engines due to their low weight and short length of combustion chamber.

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Berichte der Organisationen zum Thema "Combustion chambre"

Kellar, S. A., W. R. A. Huff, E. J. Moler, S. Yeah, and Z. Hussain. Characterization of combustion chamber products by core-level photoabsorption spectroscopy. Office of Scientific and Technical Information (OSTI), 1997. http://dx.doi.org/10.2172/603652.

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Ikeda, Takeshi, Takeshi Nakajima, Daisuke Kawai, and Yoji Fukami. Improvement of transitional characteristic by measuring pressure in the combustion chamber. SAE International, 2005. http://dx.doi.org/10.4271/2005-32-0050.

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Wherley, Brian, Don Ulmer, and Scott Claflin. Injector and Combustion Chamber Advances Demonstrated on the Thrust Cell Technologies Program. Defense Technical Information Center, 1999. http://dx.doi.org/10.21236/ada405893.

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Dols, W. Stuart. Ventilation characterization of the Consumer Product Safety Commission combustion test chamber facility. National Institute of Standards and Technology, 1990. http://dx.doi.org/10.6028/nist.ir.4415.

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Choi, Seung-hwan, Yasuo Moriyoshi, and Shigemi Kobayashi. Measurement of Local Gas Temperature Inside a Combustion Chamber Using Two-Wired Thermocouple. SAE International, 2005. http://dx.doi.org/10.4271/2005-08-0331.

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Culick, F. E. Modeling and Active Control of Nonlinear Unsteady Motions in Combustion Chambers. Defense Technical Information Center, 1996. http://dx.doi.org/10.21236/ada310960.

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Fontanesi, Stefano, Vincenzo Gagliardi, Simone Malaguti, and Enrico Mattarelli. CFD parametric analysis of the combustion chamber shape in a small HSDI Diesel engine. SAE International, 2005. http://dx.doi.org/10.4271/2005-32-0094.

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Luke, Gary, Mark Eagar, Michael Sears, Scott Felt, and Bob Prozan. Status of Advanced Two-Phase Flow Model Development for SRM Chamber Flow Field and Combustion Modeling. Defense Technical Information Center, 2004. http://dx.doi.org/10.21236/ada427829.

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Laudal, Dennis L. INVESTIGATION OF THE FATE OF MERCURY IN A COAL COMBUSTION PLUME USING A STATIC PLUME DILUTION CHAMBER. Office of Scientific and Technical Information (OSTI), 2001. http://dx.doi.org/10.2172/791725.

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Nakashima, Kenro, Munemasa Hashimoto, Shigeo Sekiyama, and Hiroshi Sasaki. Combustion and Performance of Heat-Insulated Natural Gas Engine With a Control Valve at a Pre-Chamber. SAE International, 2005. http://dx.doi.org/10.4271/2005-08-0545.

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