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Статті в журналах з теми "Propulsion spray"
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.
Повний текст джерелаBartlett, 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.
Повний текст джерелаNaghdi, 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.
Повний текст джерелаWANG, 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.
Повний текст джерелаWu, 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.
Повний текст джерелаLi, 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.
Повний текст джерелаSutrisno, 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.
Повний текст джерелаYu, 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.
Повний текст джерелаLefebvre, 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.
Повний текст джерелаVinogradov, 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.
Повний текст джерелаДисертації з теми "Propulsion spray"
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.
Повний текст джерелаThe 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
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.
Повний текст джерелаPotier, 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.
Повний текст джерелаCombustion 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
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.
Повний текст джерелаCoordenação 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
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.
Повний текст джерелаBanca: 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
Mestre
Книги з теми "Propulsion spray"
On the combustion of a laminar spray. [Washington, DC]: National Aeronautics and Space Administration, 1993.
Знайти повний текст джерелаL, 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.
Знайти повний текст джерелаAgarwal, Avinash Kumar, Saptarshi Basu, and Achintya Mukhopadhyay. Droplets and Sprays: Applications for Combustion and Propulsion. Springer, 2017.
Знайти повний текст джерелаAgarwal, Avinash Kumar, Saptarshi Basu, Achintya Mukhopadhyay, and Chetankumar Patel. Droplets and Sprays: Applications for Combustion and Propulsion. Springer, 2017.
Знайти повний текст джерелаDroplets and Sprays: Applications for Combustion and Propulsion. Springer, 2019.
Знайти повний текст джерелаЧастини книг з теми "Propulsion spray"
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.
Повний текст джерелаSarkar, 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.
Повний текст джерелаContinillo, 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.
Повний текст джерелаChakraborty, 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.
Повний текст джерелаRees, 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.
Повний текст джерелаLinne, 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.
Повний текст джерелаBasu, 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.
Повний текст джерелаIyengar, 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.
Повний текст джерелаGupta, 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.
Повний текст джерела"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.
Повний текст джерелаТези доповідей конференцій з теми "Propulsion spray"
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.
Повний текст джерелаCHIN, 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.
Повний текст джерелаCOHEN, 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.
Повний текст джерелаLadeinde, 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.
Повний текст джерелаYANG, 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.
Повний текст джерелаKIM, 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.
Повний текст джерелаROSFJORD, 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.
Повний текст джерелаCHIU, 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.
Повний текст джерелаFERRENBERG, 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.
Повний текст джерелаMcCabe, 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.
Повний текст джерела