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Academic literature on the topic 'Propulsion spray'

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Published: 10 December 2022
Last updated: 29 January 2023

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Journal articles on the topic "Propulsion spray"

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Richecoeur, Franck, and Sébastien Candel. "Combustion, spray and flow dynamics for aerospace propulsion." Comptes Rendus Mécanique 341, no. 1-2 (January 2013): 1–3. http://dx.doi.org/10.1016/j.crme.2012.11.011.

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Bartlett, C. S. "Turbine Engine Icing Spray Bar Design Issues." Journal of Engineering for Gas Turbines and Power 117, no. 3 (July 1, 1995): 406–12. http://dx.doi.org/10.1115/1.2814110.

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Techniques have been developed at the Engine Test Facility (ETF) of the Arnold Engineering Development Center (AEDC) to simulate flight through atmospheric icing conditions of supercooled liquid water droplets. Ice formed on aircraft and propulsion system surfaces during flight through icing conditions can, even in small amounts, be extremely hazardous. The effects of ice are dependent on many variables and are still unpredictable. Often, experiments are conducted to determine the characteristics of the aircraft and its propulsion system in an icing environment. Facilities at the ETF provide the capability to conduct icing testing in either the direct-connect (connected pipe) or the free-jet mode. The requirements of a spray system for turbine engine icing testing are described, as are the techniques used at the AEDC ETF to simulate flight in icing conditions. Some of the key issues facing the designer of a spray system for use in an altitude facility are identified and discussed, and validation testing of the design of a new spray system for the AEDC ETF is detailed. This spray system enables testing of the newest generation of high-thrust turbofan engines in simulated icing conditions.
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Naghdi, P. M., and M. B. Rubin. "The Effects of Energy Dissipation on the Transition to Planing of a Boat." Journal of Ship Research 33, no. 01 (March 1, 1989): 35–46. http://dx.doi.org/10.5957/jsr.1989.33.1.35.

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The problem of the transition to planing of a boat, in the presence of the effect of spray formation at the boat's leading edge, is investigated using a nonlinear steady-state solution of the equations of the theory of a directed fluid sheet for two-dimensional motion of an incompressible inviscid fluid. The motion of the fluid is coupled with the motion of the free-floating boat and detailed analysis is undertaken pertaining to such features as trim angle, sinkage, and propulsion force. The effects of the rate of energy dissipation arising from spray formation at the boat's leading edge, and changes in equilibrium depth, propulsion angle, and the boat's weight, are studied and shown to significantly influence the boat's planing characteristics.
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WANG, JIANGFENG, CHEN LIU, and YIZHAO WU. "NUMERICAL SIMULATION OF SPRAY ATOMIZATION IN SUPERSONIC FLOWS." Modern Physics Letters B 24, no. 13 (May 30, 2010): 1299–302. http://dx.doi.org/10.1142/s0217984910023475.

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With the rapid development of the air-breathing hypersonic vehicle design, an accurate description of the combustion properties becomes more and more important, where one of the key techniques is the procedure of the liquid fuel mixing, atomizing and burning coupled with the supersonic crossflow in the combustion chamber. The movement and distribution of the liquid fuel droplets in the combustion chamber will influence greatly the combustion properties, as well as the propulsion performance of the ramjet/scramjet engine. In this paper, numerical simulation methods on unstructured hybrid meshes were carried out for liquid spray atomization in supersonic crossflows. The Kelvin-Helmholtz/Rayleigh-Taylor hybrid model was used to simulate the breakup process of the liquid spray in a supersonic crossflow with Mach number 1.94. Various spray properties, including spray penetration height, droplet size distribution, were quantitatively compared with experimental results. In addition, numerical results of the complex shock wave structure induced by the presence of liquid spray were illustrated and discussed.
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Wu, Jinxin, Li Cheng, Can Luo, and Chuan Wang. "Influence of External Jet on Hydraulic Performance and Flow Field Characteristics of Water Jet Propulsion Pump Device." Shock and Vibration 2021 (May 24, 2021): 1–15. http://dx.doi.org/10.1155/2021/6690910.

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Water jet propulsion technology has broad application prospects in the field of ships, and water jet technology is a kind of high and new technology that is booming and has a wide range of applications. However, there are a few studies on the effect of the external jet on the performance of the water jet propulsion pump, and it is urgent to carry out this research. In this paper, the standard k-ε turbulence model is used to carry out the numerical simulation study of the influence of the external jet on the hydraulic performance and flow field characteristics of the water jet propulsion pump device. This paper discusses the selection of calculation models, the division of grids and the setting of turbulence models, and an in-depth analysis of the calculation results. The research results show that when a high-speed water jet enters a moving water body, it will cause turbulence in the moving water body. With the increase of jet flow, the turbulence phenomenon will be improved. The average velocity of the outlet section of the nozzle is consistent with the change of the total pressure. The average vortex gradually decreases, the turbulent kinetic energy changes little, the turbulence dissipation first decreases and then increases, and the nozzle axial force changes more and more. The axial force and thrust of the device will obviously increase when the two water streams merge and spray, and they will increase with the increase of the jet flow rate. By revealing the influence mechanism of the external jet on the water jet propulsion pump device, it can provide a theoretical basis and guiding direction for further optimizing the hydraulic performance of the entire device.
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Li, Bo, Huang Kuo, Xuehui Wang, Yiyi Chen, Yangang Wang, David Gerada, Sean Worall, Ian Stone, and Yuying Yan. "Thermal Management of Electrified Propulsion System for Low-Carbon Vehicles." Automotive Innovation 3, no. 4 (December 2020): 299–316. http://dx.doi.org/10.1007/s42154-020-00124-y.

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AbstractAn overview of current thermal challenges in transport electrification is introduced in order to underpin the research developments and trends of recent thermal management techniques. Currently, explorations of intelligent thermal management and control strategies prevail among car manufacturers in the context of climate change and global warming impacts. Therefore, major cutting-edge systematic approaches in electrified powertrain are summarized in the first place. In particular, the important role of heating, ventilation and air-condition system (HVAC) is emphasised. The trends in developing efficient HVAC system for future electrified powertrain are analysed. Then electric machine efficiency is under spotlight which could be improved by introducing new thermal management techniques and strengthening the efforts of driveline integrations. The demanded integration efforts are expected to provide better value per volume, or more power output/torque per unit with smaller form factor. Driven by demands, major thermal issues of high-power density machines are raised including the comprehensive understanding of thermal path, and multiphysics challenges are addressed whilst embedding power electronic semiconductors, non-isotropic electromagnetic materials and thermal insulation materials. Last but not least, the present review has listed several typical cooling techniques such as liquid cooling jacket, impingement/spray cooling and immersion cooling that could be applied to facilitate the development of integrated electric machine, and a mechanic-electric-thermal holistic approach is suggested at early design phase. Conclusively, a brief summary of the emerging new cooling techniques is presented and the keys to a successful integration are concluded.
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Sutrisno, Avando Bastari, and Okol Sri Suharyo. "Enviromental Pattern Analysis of Biodiesel (Castor, Coconut, MGB) to Support Alternative Energy using CFD approach." Global Journal of Engineering and Technology Advances 8, no. 1 (July 30, 2021): 051–60. http://dx.doi.org/10.30574/gjeta.2021.8.1.0100.

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The Ship uses the MTU 16V956 TB 92 propulsion engine with a piston-type Mexican Hat combustion chamber. In general, the crown is used on machines with large torque. Besides that, the crown shape in the combustion chamber is also very influential on the formation of a mixture of fuel and air before the combustion process occurs. So it is necessary to know about the spray pattern of biodiesel fuel of enviromental things (castor, coconut, used cooking oil/MGB) in the Mexican Hat combustion chamber. In this study, using the Mexican Hat-shaped piston crown simulation method, the first step was to test the spray pattern of the three types of biodiesel (castor, coconut, used cooking oil) by simulating a tube with an injection pressure of 350 bar gauge pressure inside a barometric pressure tube. While the completion in the Mexican Hat combustion chamber with a chamber pressure of 35 bar gauge and injection pressure of 350 bar gauge was completed with the CFD program, Fluent 6.2, and the results of the three biodiesels were compared. From the CFD simulation results obtained spray patterns of the three types of biodiesel (castor, coconut, used cooking oil). At the same injection pressure and chamber pressure, used cooking biodiesel has the longest penetration length, followed by castor biodiesel and coconut biodiesel. The spray angle of coconut biodiesel is the largest, followed by castor biodiesel and used cooking oil biodiesel. SMD coconut biodiesel is the smallest, followed by castor biodiesel and used cooking oil biodiesel.
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Yu, Weigang, Zhiqing Zhang, and Bo Liu. "Investigation on the Performance Enhancement and Emission Reduction of a Biodiesel Fueled Diesel Engine Based on an Improved Entire Diesel Engine Simulation Model." Processes 9, no. 1 (January 6, 2021): 104. http://dx.doi.org/10.3390/pr9010104.

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In order to improve the efficiency of the diesel engine and reduce emissions, an improved heat transfer model was developed in an AVL-BOOST environment which is a powerful and user-friendly software for engine steady-state and transient performance analysis. The improved heat transfer model considers the advantages of the Woschni1978 heat transfer model and Honhenberg heat transfer model. In addition, a five-component biodiesel skeletal mechanism containing 475 reactions and 134 species was developed to simulate the fuel spray process and combustion process since it contained methyl linolenate, methyl linoleate, methyl oleate, methyl stearate, and methyl palmitate, which are a majority component in most biodiesel. Finally, the propulsion and load characteristics of a diesel engine fueled with biodiesel fuel were investigated by the improved heat transfer model in term of power, brake specific fuel consumption (BSFC), soot and NOx emissions. Similarly, the effects of the fuel injection rate on the diesel engine’s characteristic fueled with biodiesel was studied. The result showed that the errors between experiment and simulation were less than 2%. Thus, the simulation model could predict the propulsion and load characteristics of the diesel engine. The nozzle diameter, injection pressure, and injection advance angle are significant to the injection system. Thus, it is very important to choose the injection rate reasonably.
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Lefebvre, A. H. "Fuel Effects on Gas Turbine Combustion—Ignition, Stability, and Combustion Efficiency." Journal of Engineering for Gas Turbines and Power 107, no. 1 (January 1, 1985): 24–37. http://dx.doi.org/10.1115/1.3239693.

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An analytical study is made of the substantial body of experimental data acquired during recent Wright-Patterson Aero Propulsion Laboratory sponsored programs on the effects of fuel properties on the performance and reliability of several gas turbine combustors, including J79-17A, J79–17C (Smokeless), F101, TF41, TF39, J85, TF33, and F100. Quantitative relationships are derived between certain key aspects of combustion, notably combustion efficiency, lean blowout limits and lean light-off limits, and the relevant fuel properties, combustor design features, and combustor operating conditions. It is concluded that combustion efficiency, lean blowout limits, and lean lightoff limits are only slightly dependent on fuel chemistry, but are strongly influenced by the physical fuel properties that govern atomization quality and spray evaporation rates.
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Vinogradov, Viacheslav A., Yurii M. Shikhman, and Corin Segal. "A Review of Fuel Pre-injection in Supersonic, Chemically Reacting Flows." Applied Mechanics Reviews 60, no. 4 (July 1, 2007): 139–48. http://dx.doi.org/10.1115/1.2750346.

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Developing an efficient, supersonic combustion-based, air breathing propulsion cycle operating above Mach 3.5, especially when conventional hydrocarbon fuels are sought and particularly when liquid fuels are preferred to increase density, requires mostly effective mechanisms to improve mixing efficiency. One way to extend the time available for mixing is to inject part of the fuel upstream of the vehicle’s combustion chamber. Injection from the wall remains one of the most challenging problems in supersonic aerodynamics, including the requirement to minimize impulse losses, improve fuel-air mixing, reduce inlet∕combustor interactions, and promote flame stability. This article presents a review of studies involving liquid and, in selected cases, gaseous fuel injected in supersonic inlets or in combustor’s insulators. In all these studies, the fuel was injected from a wall in a wake of thin swept pylons at low dynamic pressure ratios (qjet∕qair=0.6–1.5), including individual pylon∕injector geometries and combinations in the inlet and combustor’s isolator, a variety of injection conditions, different injectants, and evaluated their effects on fuel plume spray, impulse losses, and mixing efficiency. This review article cites 47 references.
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Dissertations / Theses on the topic "Propulsion spray"

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Sibra, Alaric. "Modélisation et étude de l’évaporation et de la combustion de gouttes dans les moteurs à propergol solide par une approche eulérienne Multi-Fluide." Thesis, Université Paris-Saclay (ComUE), 2015. http://www.theses.fr/2015SACLC019/document.

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En propulsion solide, l'ajout de particules d'aluminium dans le propergol améliore de façon significative les performances du moteur grâce à une augmentation sensible de la température de chambre. La présence de gouttes d'aluminium et de résidus d'alumine de différentes tailles et en quantité importante a un impact notoire sur le fonctionnement du moteur. Dans cette optique, nous souhaitons obtenir une meilleure prévision de la stabilité de fonctionnement en cas de déclenchement d'instabilités d'origine aéroacoustique ou thermoacoustique. Nous visons des calculs plus précis de l'étendue de la zone de combustion, de la chaleur dégagée par la combustion distribuée des gouttes et de la distribution en taille des résidus. Nos efforts ont porté sur la modélisation des échanges entre la phase gazeuse et cette phase dispersée composée de gouttes de nature et de taille très diverses. Le paramètre taille pilotant la dynamique du spray et le couplage avec le gaz, le suivi précis des changements de taille est un enjeu majeur.Dans cette contribution, nous avons choisi une approche cinétique pour la description des sprays polydisperses. L'équation cinétique de Williams-Boltzmann utilisée pour suivre l'évolution des propriétés du spray est résolue par une approche eulérienne. Les méthodes Multi-Fluide (MF) traitent naturellement les changements de taille tels que l'évaporation et la coalescence. Ces méthodes reposent sur une intégration continue de la variable taille sur des intervalles fixes appelés sections sur lesquels nous pouvons dériver des systèmes d'équations de conservation. Chaque système est vu comme un fluide qui est en couplage fort avec la phase gazeuse via des termes sources.Nous avons travaillé sur une méthode MF à deux moments en taille basée sur une famille de fonctions de forme polynomiale pour reconstruire la distribution en taille au sein des sections. Cette approche d'ordre deux en temps et en espace s'avère performante car elle décrit avec précision l'évolution de la distribution avec un nombre modéré de sections. Un travail original a été mené afin d'étendre l'approche MF à des gouttes bicomposants. Cette méthode ouvre la voie à des modèles de combustion des gouttes d'aluminium plus représentatifs. Dans le contexte des simulations instationnaires, nous avons porté une attention particulière à l'emploi d'une stratégie numérique robuste et précise pour le couplage entre les phases modélisées par une approche Euler-Euler. Nous montrons qu'une méthode de splitting séparant le traitement du transport des phases gazeuse/dispersée de celui des termes sources est particulièrement adaptée pour la résolution d'un problème multi-échelle spatial et temporel. Dans la mesure où les conditions de réalisabilité sur les moments en taille des méthodes MF ne sont pas garanties avec des méthodes d'intégration traditionnelles, nous avons développé des schémas innovants pour l'intégration des termes sources. Les travaux proposés dans cette contribution répond à deux exigences : 1- un ratio coût/précision attractif pour des simulations industrielles 2- une facilité d'implémentation des méthodes et une modularité assurant la pérennisation des codes industriels. Ces développements ont d'abord été vérifiés à l'aide d'un code ad hoc ; des cas test d'étude d'acoustique diphasique linéaire ont notamment souligné la pertinence de la technique de splitting pour restituer avec précision les interactions spray-acoustique. Les nouvelles méthodes ont ensuite été implémentées et validées au sein du code multi-physique CEDRE développé à l'ONERA. Des calculs de propulsion solide sur des configurations moteur réalistes ont finalement mis en évidence le niveau de maturité atteint par les méthodes eulériennes pour décrire avec fidélité la dynamique des sprays polydisperses. Les résultats de ces simulations ont mis en avant la sensibilité des niveaux d'instabilités en fonction de la distribution en taille des gouttes d'aluminium et des résidus
The addition of a significant mass fraction of aluminum particle in the propellant of Solid Rocket Motors improves performance through an increase of the temperature in the combustion chamber. The distributed combustion of aluminum droplets in a portion of the chamber yields a massive amount of disperse aluminum oxide residues with a large size spectrum, called a polydisperse spray, in the entire volume. The spray can have a significant impact on the motor behavior and in particular on the onset/damping of instability. When dealing with aeroacoustical and thermoacoustical instabilities, the faithful prediction of the interactions between the gaseous phase and the spray is a determining step for understanding the physical mechanisms and for future solid rocket motor optimization. In such a harsh environment, experimental measurements have a hard time providing detailed explanation of the physical mechanisms and one has to resort to numerical simulation. For such a purpose, the distributed combustion zone and thermal profile therein, the heat generated by the combustion of the dispersed droplets and the large size distribution of the aluminum oxide residues and its coupling with he gaseous phase hydrodynamic and acoustic fields have to be accurately reproduced through a proper level of modeling and a high fidelity simulation including a precise resolution of size polydispersity, which is a key parameter.In this contribution, we choose a kinetic approach for the description of polydisperse sprays. The Williams-Boltzmann Equation is used to model the disperse phase and we derive a fully Eulerian approach through moment methods. The Multi-Fluid (MF) methods naturally treat droplet size evolution through phenomena such as evaporation and coalescence. These methods rely on the conservation of size moments on fixed intervals called sections and yield systems of conservation laws for a set of "fluids" of droplet of various sizes, which is strongly coupled with the gas phase via source terms. We derive a new optimal and flexible Two Size Moment MF method based on a family of polynomial reconstruction functions to describe the size distribution in the sections, which is second order accurate and particularly efficient at describing accurately the evolution of the size distribution with a moderate number of sections. An original work is also conducted in order to extend this approach to two-component droplets. For size moment MF methods, realizability of the moments is a crucial issue. Thus, we have developed innovative schemes for integrating source terms in moment conservation equations describing transport in phase space. This method enables the use of more representative aluminum droplet combustion models, and leads to more advanced studies of the distributed combustion zone. Moreover, for unsteady two-phase flow simulations, we have developed a robust and accurate coupling strategy between phases that are modeled by a fully Eulerian approach based on operator splitting in order to treat such spatial and temporal very multi-scale problems with reasonable computational time. All the proposed developments have been carried out following two criteria : 1- an attractive cost/accuracy ratio for industrial simulations in the context of high fidelity simulations 2- a preservation of industrial code legacy. Verification of the models and methods have been conducted first using an in-house reseach code and then in the context of a two-phase acoustic study thus emphasizing the relevance of the splitting technique to capture accurately spray-acoustic interactions
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Sharma, Arvindh R. "Liquid Jet in Oscillating Crossflow: Characterization of Near-Field and Far-Field Spray Behavior." University of Cincinnati / OhioLINK, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1439281517.

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Potier, Luc. "Large Eddy Simulation of the combustion and heat transfer in sub-critical rocket engines." Thesis, Toulouse, INPT, 2018. http://www.theses.fr/2018INPT0043/document.

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La combustion cryogénique dans les moteurs de fusée dits à propulsion liquide utilise généralement un couple d'ergols, le plus couramment composé d'hydrogène/oxygène (H2/O2). Privilégiée pour le fort pouvoir calorifique du dihydrogène, cette combustion à haute pression, induit des températures de fonctionnement très élevées et nécessite l'intégration d'un système de refroidissement. La prédiction des flux thermiques aux parois est donc un élément essentiel de la conception d'une chambre de combustion de moteur fusée. Ces flux sont le résultat d'écoulements fortement turbulents, compressibles, avec une cinétique chimique violente induisant de forts gradients d'espèces et de température. La simulation de ces phénomènes nécessite des approches spécifiques telles que la Simulation aux Grandes Echelles (SGE) qui réalise un très bon compromis entre précision et coût de calcul. Cette thèse a ainsi pour objectif la simulation par SGE des transferts de chaleur aux parois dans les chambres de combustion de moteurs fusée opérant en régime sous-critique. Le régime sous-critique implique un état liquide pour un des ergols, dont il faut traiter l'injection et l'atomisation. Dans un premier temps ce travail s'intéresse à plusieurs éléments de modélisation nécessaire pour réaliser les simulations visées. Le comportement des flammes H2/O2 est décrit par un schéma cinétique réduit et validé sur des configurations académiques. La prédictivité de ce schéma est évaluée sur une large gamme de fonctionnement dans des conditions représentatives des moteurs fusée. La simulation de l'injection de l'oxygène liquide (LOx) est un autre point critique qui nécessite de décrire l'atomisation et la phase dispersée ainsi que son couplage avec la phase gazeuse. La déstabilisation et l'atomisation primaire du jet liquide, trop complexe à simuler en SGE 3D, sont omises ici pour injecter directement un spray paramétré grâce à des corrélations empiriques. Enfin, la prédiction des flux thermiques utilise un modèle de loi de paroi spécifiquement dédiée aux écoulements à fort gradient de température. Cette loi de paroi est validée sur des configurations de canaux turbulents par comparaison avec des simulations avec résolution directe de la couche limite. La méthodologie basée sur les modèles développés est ensuite employée pour la simulation d'une chambre de combustion représentative du fonctionnement des moteurs cryogéniques. Il s'agit de la configuration CONFORTH testée sur le banc MASCOTTE (ONERA) et pour laquelle des mesures de température de paroi et de flux thermiques sont disponibles. Les résultats des SGE montrent un bon accord avec l'expérience et démontrent la capacité de la SGE à prédire les flux thermiques dans une chambre de combustion de moteur fusée. Enfin, dans un dernier chapitre ce travail s'intéresse à une méthode d'augmentation des transferts thermiques via une expérience de JAXA utilisant des parois rainurées dans la direction axiale. Par comparaison avec une chambre à parois lisses, les résultats démontrent la bonne prédiction par la SGE de l'augmentation du flux de chaleur grâce aux rainures et confirment la validité de la méthode développée pour des géométries de paroi complexes
Combustion in cryogenic engines is a complex phenomenon, involving either liquid or supercritical fluids at high pressure, strong and fast oxidation chemistry, and high turbulence intensity. Due to extreme operating conditions, a particularly critical issue in rocket engine is wall heat transfer which requires efficient cooling of the combustor walls. The concern goes beyond material resistance: heat fluxes extracted through the chamber walls may be reused to reduce ergol mass or increase the power of the engine. In expander-type engine cycle, this is even more important since the heat extracted by the cooling system is used to drive the turbo-pumps that feed the chamber in fuel and oxidizer. The design of rocket combustors requires therefore an accurate prediction of wall heat flux. To understand and control the physics at play in such combustor, the Large Eddy Simulation (LES) approach is an efficient and reliable numerical tool. In this thesis work, the objective is to predict wall fluxes in a subcritical rocket engine configuration by means of LES. In such condition, ergols may be in their liquid state and it is necessary to model liquid jet atomization, dispersion and evaporation.The physics that have to be treated in such engine are: highly turbulent reactive flow, liquid jet atomization, fast and strong kinetic chemistry and finally important wall heat fluxes. This work first focuses on several modeling aspects that are needed to perform the target simulations. H2/O2 flames are driven by a very fast chemistry, modeled with a reduced mechanism validated on academic configurations for a large range of operating conditions in laminar pre- mixed and non-premixed flames. To form the spray issued from the atomization of liquid oxygen (LOx) an injection model is proposed based on empirical correlations. Finally, a wall law is employed to recover the wall fluxes without resolving directly the boundary layer. It has been specifically developed for important temperature gradients at the wall and validated on turbulent channel configurations by comparison with wall resolved LES. The above models are then applied first to the simulation of the CONFORTH sub-scale thrust chamber. This configuration studied on the MASCOTTE test facility (ONERA) has been measured in terms of wall temperature and heat flux. The LES shows a good agreement compared to experiment, which demonstrates the capability of LES to predict heat fluxes in rocket combustion chambers. Finally, the JAXA experiment conducted at JAXA/Kakuda space center to observe heat transfer enhancement brought by longitudinal ribs along the chamber inner walls is also simulated with the same methodology. Temperature and wall fluxes measured with smooth walls and ribbed walls are well recovered by LES. This confirms that the LES methodology proposed in this work is able to handle wall fluxes in complex geometries for rocket operating conditions
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Melo, Hugo Henrique Tinoco [UNESP]. "Análise dos sprays de jatos de injetores de motor foguete utilizando um sistema de processamento digital de imagens." Universidade Estadual Paulista (UNESP), 2011. http://hdl.handle.net/11449/97043.

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Made available in DSpace on 2014-06-11T19:28:33Z (GMT). No. of bitstreams: 0 Previous issue date: 2011-08-22Bitstream added on 2014-06-13T20:58:28Z : No. of bitstreams: 1 melo_hht_me_guara.pdf: 1759227 bytes, checksum: 3dfd437259b41c05e4944f9e56da28d5 (MD5)
Coordenação de Aperfeiçoamento de Pessoal de Nível Superior (CAPES)
A utilização de imagens digitais para extrair informações de objetos tem sido uma solução amplamente empregada em pesquisas científicas e em processos industriais. A contínua redução nos preços de equipamentos, a facilidade do uso de softwares e a simples integração com recursos de informática tem feito que muitos processos migrem para esta solução mais ágil, confiável e econômica. A indústria aeroespacial, que possui uma cadeia de produção não contínua e exige a avaliação de todos os seus componentes para obtenção de um nível de confiança elevado, encontra no emprego do processamento digital de imagens uma solução versátil e eficaz para análise das características de cada componente. Neste trabalho é apresentado um programa, desenvolvido em LabVIEW™, para medição dos sprays cônicos de jatos de injetores de motor foguete utilizando um sistema de processamento digital de imagens para sua análise. São apresentadas também as metodologias até então utilizadas para efetuar este tipo de medida. Os sprays dos jatos são desenvolvidos na saída do injetor, são exibidos visualmente durante o teste hidráulico a frio e tem influência direta no desempenho do motor foguete. A utilização desta nova ferramenta permitiu a realização desta medida de forma automática, com o fornecimento da incerteza de medição em níveis de confiança pré-estabelecido e mostrou-se ser mais exata e precisa que as metodologias anteriores
The usage of digital images to extract information from objects has been a solution widely used in scientific research and in industrial processes. The continued reduction in prices of equipment, the facility of software manipulation and the simple integration with computing resources has done many processes to migrate to this more flexible, reliable and economical solution. The aerospace industry, which has a chain of production that is not continuous and requires the evaluation of all its components to obtain a high confidence level, finds in the usage of digital image processing a versatile and effective solution for analysis of the characteristics of each component . This paper presents a program developed in LabVIEW™, to measure the rocket engine conic spray jet by using a digital image processing system for analysis. It is also presented the methodologies previously used to perform this type of measurement. The jet sprays are developed at the exit of the injector, are displayed visually during the cold hydraulic test and it has directly influences on the performance of the rocket engines. The usage of this new tool allowed us to make the measurement automatically with the supply of uncertainty together with a pre-established confidence level and it proved to be more accurate and precise than previous methodologies
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Melo, Hugo Henrique Tinoco. "Análise dos sprays de jatos de injetores de motor foguete utilizando um sistema de processamento digital de imagens /." Guaratinguetá : [s.n.], 2011. http://hdl.handle.net/11449/97043.

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Orientador: Fernando de Azevedo Silva
Banca: João Zangrandi Filho
Banca: Silvana Aparecida Barbosa
Resumo: A utilização de imagens digitais para extrair informações de objetos tem sido uma solução amplamente empregada em pesquisas científicas e em processos industriais. A contínua redução nos preços de equipamentos, a facilidade do uso de softwares e a simples integração com recursos de informática tem feito que muitos processos migrem para esta solução mais ágil, confiável e econômica. A indústria aeroespacial, que possui uma cadeia de produção não contínua e exige a avaliação de todos os seus componentes para obtenção de um nível de confiança elevado, encontra no emprego do processamento digital de imagens uma solução versátil e eficaz para análise das características de cada componente. Neste trabalho é apresentado um programa, desenvolvido em LabVIEW™, para medição dos sprays cônicos de jatos de injetores de motor foguete utilizando um sistema de processamento digital de imagens para sua análise. São apresentadas também as metodologias até então utilizadas para efetuar este tipo de medida. Os sprays dos jatos são desenvolvidos na saída do injetor, são exibidos visualmente durante o teste hidráulico a frio e tem influência direta no desempenho do motor foguete. A utilização desta nova ferramenta permitiu a realização desta medida de forma automática, com o fornecimento da incerteza de medição em níveis de confiança pré-estabelecido e mostrou-se ser mais exata e precisa que as metodologias anteriores
Abstract: The usage of digital images to extract information from objects has been a solution widely used in scientific research and in industrial processes. The continued reduction in prices of equipment, the facility of software manipulation and the simple integration with computing resources has done many processes to migrate to this more flexible, reliable and economical solution. The aerospace industry, which has a chain of production that is not continuous and requires the evaluation of all its components to obtain a high confidence level, finds in the usage of digital image processing a versatile and effective solution for analysis of the characteristics of each component . This paper presents a program developed in LabVIEW™, to measure the rocket engine conic spray jet by using a digital image processing system for analysis. It is also presented the methodologies previously used to perform this type of measurement. The jet sprays are developed at the exit of the injector, are displayed visually during the cold hydraulic test and it has directly influences on the performance of the rocket engines. The usage of this new tool allowed us to make the measurement automatically with the supply of uncertainty together with a pre-established confidence level and it proved to be more accurate and precise than previous methodologies
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Books on the topic "Propulsion spray"

1

On the combustion of a laminar spray. [Washington, DC]: National Aeronautics and Space Administration, 1993.

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L, Bulzan Daniel, and United States. National Aeronautics and Space Administration., eds. On the combustion of a laminar spray. [Washington, DC]: National Aeronautics and Space Administration, 1993.

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Agarwal, Avinash Kumar, Saptarshi Basu, and Achintya Mukhopadhyay. Droplets and Sprays: Applications for Combustion and Propulsion. Springer, 2017.

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Agarwal, Avinash Kumar, Saptarshi Basu, Achintya Mukhopadhyay, and Chetankumar Patel. Droplets and Sprays: Applications for Combustion and Propulsion. Springer, 2017.

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Droplets and Sprays: Applications for Combustion and Propulsion. Springer, 2019.

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Book chapters on the topic "Propulsion spray"

1

Sarkar, Sourav, Joydeep Munshi, Santanu Pramanik, Achintya Mukhopadhyay, and Swarnendu Sen. "Interaction of Water Spray with Flame." In Energy for Propulsion, 151–86. Singapore: Springer Singapore, 2018. http://dx.doi.org/10.1007/978-981-10-7473-8_7.

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Sarkar, Sourav, Joydeep Munshi, Achintya Mukhopadhyay, and Swarnendu Sen. "Polydisperse Spray Modeling Using Eulerian Method." In Sustainable Development for Energy, Power, and Propulsion, 481–502. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-5667-8_19.

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Continillo, G., and W. A. Sirignano. "Unsteady, Spherically-Symmetric Flame Propagation Through Multicomponent Fuel Spray Clouds." In Modern Research Topics in Aerospace Propulsion, 173–98. New York, NY: Springer New York, 1991. http://dx.doi.org/10.1007/978-1-4612-0945-4_10.

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Chakraborty, Arnab, Mithun Das, Srikrishna Sahu, and Dalton Maurya. "A Parametric Study on Rotary Slinger Spray Characteristics Using Laser Diagnostics." In Proceedings of the National Aerospace Propulsion Conference, 615–28. Singapore: Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-2378-4_36.

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Rees, Andreas, and Michael Oschwald. "Experimental Investigation of Transient Injection Phenomena in Rocket Combusters at Vacuum with Cryogenic Flash Boiling." In Fluid Mechanics and Its Applications, 211–31. Cham: Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-031-09008-0_11.

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AbstractThe substitution of the toxic hydrazine in current high-altitude rocket engines like upper stages or reaction control thrusters by green propellants is a major key driver in the current technology development of rocket propulsion systems. Operating these kind of rocket engines at high-altitude leads to a sudden pressure drop in the liquid propellants during their injection into the combustion chamber with a near-vacuum atmosphere prior to ignition. The resulting superheated thermodynamic state of the liquid causes a fast and eruptive evaporation which is called flash boiling. The degree of atomisation is important for a successful ignition and a secure operation of the rocket engine. The development and operation of a cryogenic high-altitude test bench at DLR Lampoldshausen enables the systematical experimental characterization of cryogenic flash boiling due to its ability to adjust and control the injection parameters like temperature, pressure or geometry. Several test campaigns with liquid nitrogen (LN2) were performed using two optical diagnostic methods: First, flash boiling LN2 spray patterns were visualised by means of high-speed shadowgraphy and, secondly, we determined the droplet size and velocity distributions in strongly superheated LN2 sprays with the help of a laser-based Phase Doppler system (PDA). The experimental data generated within these measurement campaigns provide defined boundary conditions as well as a broad data base for the numerical modelling of cryogenic flash boiling like e.g. the publications [8, 9].
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Linne, Mark, Zachary Falgout, and Mattias Rahm. "Optical Diagnostics for Sprays at High Pressure." In High-Pressure Flows for Propulsion Applications, 111–56. Reston, VA: American Institute of Aeronautics and Astronautics, Inc., 2020. http://dx.doi.org/10.2514/5.9781624105814.0111.0156.

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Basu, Saptarshi, Avinash Kumar Agarwal, Achintya Mukhopadhyay, and Chetankumar Patel. "Introduction to Droplets and Sprays: Applications for Combustion and Propulsion." In Energy, Environment, and Sustainability, 3–6. Singapore: Springer Singapore, 2017. http://dx.doi.org/10.1007/978-981-10-7449-3_1.

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Iyengar, Venkat S., K. Sathiyamoorthy, J. Srinivas, P. Pratheesh Kumar, and P. Manjunath. "Measurements of Droplet Velocity Fields in Sprays from Liquid Jets Injected in High-Speed Crossflows Using PIV." In Proceedings of the National Aerospace Propulsion Conference, 93–102. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-5039-3_5.

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Gupta, A. K., B. Habibzadeh, S. Archer, and M. Linck. "CONTROL OF FLAME STRUCTURE IN SPRAY COMBUSTION." In Combustion Processes in Propulsion, 129–38. Elsevier, 2006. http://dx.doi.org/10.1016/b978-012369394-5/50016-0.

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"SPRAY FLAME CHARACTERISTICS WITH STEAM-ASSISTED ATOMIZATION." In Advances in Chemical Propulsion, 285–300. CRC Press, 2001. http://dx.doi.org/10.1201/9781420040685-18.

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Conference papers on the topic "Propulsion spray"

1

Yi, Ran, Xu Zhang, Tao Yang, and Chen-Pin Chen. "Spray Flamelet Modeling of Kerosene Spray Combustion." In AIAA Propulsion and Energy 2019 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2019. http://dx.doi.org/10.2514/6.2019-3867.

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CHIN, J. "Spray research in BIAA." In 22nd Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-1730.

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COHEN, J., and T. ROSFJORD. "Spray patternation at high pressure." In 25th Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2323.

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Ladeinde, Foluso, and Ken Alabi. "Dynamics of Supersonic Spray Combustion." In 2018 Joint Propulsion Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-4743.

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YANG, G., and J. CHIN. "Experimental and analytical study on the spray characteristics of fuel sprays in heated airstream." In 23rd Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-1958.

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KIM, Y., R. HALLIT, and T. CHUNG. "Turbulent spray combustion using finite elements." In 25th Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2438.

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ROSFJORD, T., and S. RUSSELL. "Influences on fuel spray circumferential uniformity." In 23rd Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-2135.

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CHIU, H., W. CHEN, and T. JIANG. "Droplet laws in spray combustion processes." In 27th Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-2313.

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FERRENBERG, A., and M. VARMA. "Atomization data for spray combustion modeling." In 21st Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-1316.

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McCabe, Jonathan, and Millicent Coil. "A Graphical Spray Analysis Method for Gel Spray Characterization." In 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-6823.

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