Bibliografías temáticas / Rocket Combustor

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Literatura académica sobre el tema "Rocket Combustor"

Autor: Grafiati
Publicado: 4 de junio de 2021
Última modificación: 4 de febrero de 2022

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Artículos de revistas sobre el tema "Rocket Combustor"

1

Hu, Jichao, Juntao Chang, and Wen Bao. "Ignition and Flame Stabilization of a Strut-Jet RBCC Combustor with Small Rocket Exhaust." Scientific World Journal 2014 (2014): 1–6. http://dx.doi.org/10.1155/2014/675498.

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A Rocket Based Combined Cycle combustor model is tested at a ground direct connected rig to investigate the flame holding characteristics with a small rocket exhaust using liquid kerosene. The total temperature and the Mach number of the vitiated air flow, at exit of the nozzle are 1505 K and 2.6, respectively. The rocket base is embedded in a fuel injecting strut and mounted in the center of the combustor. The wall of the combustor is flush, without any reward step or cavity, so the strut-jet is used to make sure of the flame stabilization of the second combustion. Mass flow rate of the keros
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2

Li, Chaolong, Zhixun Xia, Likun Ma, Xiang Zhao, and Binbin Chen. "Numerical Study on the Solid Fuel Rocket Scramjet Combustor with Cavity." Energies 12, no. 7 (2019): 1235. http://dx.doi.org/10.3390/en12071235.

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Scramjet based on solid propellant is a good supplement for the power device of future hypersonic vehicles. A new scramjet combustor configuration using solid fuel, namely, the solid fuel rocket scramjet (SFRSCRJ) combustor is proposed. The numerical study was conducted to simulate a flight environment of Mach 6 at a 25 km altitude. Three-dimensional Reynolds-averaged Navier–Stokes equations coupled with shear stress transport (SST) k − ω turbulence model are used to analyze the effects of the cavity and its position on the combustor. The feasibility of the SFRSCRJ combustor with cavity is dem
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3

Lee, Y. W., and T. L. Jiang. "Effects of Fuel Impingement-Cooling on the Combustion Flow in a Small Bipropellant Liquid Rocket Thruster." Journal of Mechanics 31, no. 2 (2015): 161–70. http://dx.doi.org/10.1017/jmech.2014.81.

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ABSTRACTIn the present study, a three-dimensional computer code, based on the computer software KIVA-3, was developed for the combustion-flow simulation of a bipropellant liquid rocket thruster. A jets-impingement model is proposed for the unlike-doublet jet impingement issue. The computer code is employed to simulate a small bipropellant liquid rocket engine installed with three unlike-doublet injectors of NTO and MMH as well as six fuel injectors injecting MMH toward the combustor wall for cooling. Effects of the fuel-injection cooling on the combustion flow, combustion efficiency, and wall
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Shi, Lei, Da Gao, Liangliang Xing, Fei Qin, and Guoqiang He. "Numerical Study on Thermal Choke Behaviors Driven by Various Rocket Operations in an RBCC Engine in Ramjet Mode." International Journal of Turbo & Jet-Engines 37, no. 3 (2020): 305–17. http://dx.doi.org/10.1515/tjj-2019-0012.

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AbstractThermal choke is commonly employed in a fixed geometry RBCC combustor to eliminate the need for physically variable exit geometry. This paper proposed detailed numerical studies based on a two-dimensional integration model to characterize thermal choke behaviors driven by various embedded rocket operations in an RBCC engine at Mach 4 in ramjet mode. The influences of different embedded rocket operations as well as the corresponding secondary fuel injection adjustment on thermal choke generation process, the related thermal throat feature, and the engine performance are analyzed. Operat
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5

Jin, Xuan, Chibing Shen, Rui Zhou, and Xinxin Fang. "Effects of LOX Particle Diameter on Combustion Characteristics of a Gas-Liquid Pintle Rocket Engine." International Journal of Aerospace Engineering 2020 (September 15, 2020): 1–16. http://dx.doi.org/10.1155/2020/8867199.

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LOX/GCH4 pintle injector is suitable for variable-thrust liquid rocket engines. In order to provide a reference for the later design and experiments, three-dimensional numerical simulations with the Euler-Lagrange method were performed to study the effect of the initial particle diameter on the combustion characteristics of a LOX/GCH4 pintle rocket engine. Numerical results show that, as the momentum ratio between the radial LOX jet and the axial gas jet is 0.033, the angle between the LOX particle trace and the combustor axial is very small. Due to the large recirculation zones, premixed comb
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Tamanampudi, Gowtham Manikanta Reddy, Swanand Sardeshmukh, William Anderson, and Cheng Huang. "Combustion instability modeling using multi-mode flame transfer functions and a nonlinear Euler solver." International Journal of Spray and Combustion Dynamics 12 (January 2020): 175682772095032. http://dx.doi.org/10.1177/1756827720950320.

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Modern methods for predicting combustion dynamics in high-pressure combustors range from high-fidelity simulations of sub-scale model combustors, mostly for validation purposes or detailed investigations of physics, to linearized, acoustics-based analysis of full-scale practical combustors. Whereas the high-fidelity simulations presumably capture the detailed physics of mixing and heat addition, computational requirements preclude their application for practical design analysis. The linear models that are used during design typically use flame transfer functions that relate the unsteady heat a
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Yuan, Lei, and Chibing Shen. "Computational investigation on combustion instabilities in a rocket combustor." Acta Astronautica 127 (October 2016): 634–43. http://dx.doi.org/10.1016/j.actaastro.2016.06.015.

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Hossain, Mohammad A., Ahsan Choudhuri, and Norman Love. "Design of an optically accessible turbulent combustion system." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 233, no. 1 (2018): 336–49. http://dx.doi.org/10.1177/0954406218757565.

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In order to design the next generation of gas turbine combustors and rocket engines, understanding the flame structure at high-intensity turbulent flows is necessary. Many experimental studies have focused on flame structures at relatively low Reynolds and Damköhler numbers, which are useful but do not help to provide a deep understanding of flame behavior at gas turbine and rocket engine operating conditions. The current work is focused on the presentation of the design and development of a high-intensity (Tu = 15–30%) turbulent combustion system, which is operated at compressible flow regime
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Gröning, Stefan, Justin S. Hardi, Dmitry Suslov, and Michael Oschwald. "Injector-Driven Combustion Instabilities in a Hydrogen/Oxygen Rocket Combustor." Journal of Propulsion and Power 32, no. 3 (2016): 560–73. http://dx.doi.org/10.2514/1.b35768.

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Richards, G. A., and M. C. Janus. "Characterization of Oscillations During Premix Gas Turbine Combustion." Journal of Engineering for Gas Turbines and Power 120, no. 2 (1998): 294–302. http://dx.doi.org/10.1115/1.2818120.

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The use of premix combustion in stationary gas turbines can produce very low levels of Nox emissions. This benefit is widely recognized, but turbine developers routinely encounter problems with combustion oscillations during the testing of new premix combustors. Because of the associated pressure fluctuations, combustion oscillations must be eliminated in a final combustor design. Eliminating these oscillations is often time-consuming and costly because there is no single approach to solve an oscillation problem. Previous investigations of combustion stability have focused on rocket applicatio
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Tesis sobre el tema "Rocket Combustor"

1

Stowe, Robert Alan. "Performance prediction of a ducted rocket combustor." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 2001. http://www.collectionscanada.ca/obj/s4/f2/dsk3/ftp04/NQ65434.pdf.

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Hewitt, Patrick. "Numerical Modeling of a Ducted Rocket Combustor With Experimental Validation." Diss., Virginia Tech, 2008. http://hdl.handle.net/10919/28928.

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The present work was conducted with the intent of developing a high-fidelity numerical model of a unique combustion flow problem combining multi-phase fuel injection with substantial momentum and temperature into a highly complex turbulent flow. This important problem is very different from typical and more widely known liquid fuel combustion problems and is found in practice in pulverized coal combustors and ducted rocket ramjets. As the ducted rocket engine cycle is only now finding widespread use, it has received little research attention and was selected as a representative problem for thi
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3

Yakin, Bülent. "Combustor and nozzle effects on particulate behavior in solid rocket motors /." Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1993. http://handle.dtic.mil/100.2/ADA277304.

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Yakin, Bulent. "Combustor and nozzle effects on particulate behavior in solid rocket motors." Thesis, Monterey, California. Naval Postgraduate School, 1993. http://hdl.handle.net/10945/39764.

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Approved for public release; distribution is unlimited.<br>An investigation was conducted using a subscale solid rocket motor to measure the effect of nozzle residence time on the behavior of Al203 particles to assess the applicability of subscale motor data to full-scale motors and to measure the effects of nozzle entrance particle size distribution on the slag accumulated with submerged nozzles. Although particles as large as 140 micrometers were present at the nozzle entrance, most of the particulate mass was contained in much smaller particles. This observation is in good agreement with th
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Sarwade, Rohit Foster Winfred A. "Life prediction analysis of a subscale rocket engine combustor using a fluid-thermal-structural model." Auburn, Ala., 2006. http://repo.lib.auburn.edu/2006%20Spring/master's/SARWADE_ROHIT_49.pdf.

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Matta, Lawrence Mark. "Investigation of the flow turning loss in unstable solid propellant rocket motors." Diss., Georgia Institute of Technology, 1993. http://hdl.handle.net/1853/15938.

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Kutrieb, Joshua M. "Rocket plume tomography of combustion species." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2001. http://handle.dtic.mil/100.2/ADA399398.

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Thesis (M.S. in Astronautical Engineering, Aeronautical and Astronautical Engineer) Naval Postgraduate School, Dec. 2001.<br>Thesis advisors: Christopher Brophy, Jose Sinibaldi, Ashok Gopinath. "December 2001." Includes bibliographical references (p. 73). Also available in print.
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Noonan, Erin E. (Erin Elizabeth) 1978. "Structural analysis of the MIT Micro Rocket Combustion Chamber." Thesis, Massachusetts Institute of Technology, 2002. http://hdl.handle.net/1721.1/8127.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2002.<br>"June 2002."<br>Includes bibliographical references (p. 209-211).<br>The micro rocket is one of several power microelectromechanical systems (MEMS) under development at MIT. The micro rocket is experiencing structural failures at operating parameters far below the designed performance level. The deterministic strength of brittle materials, such as silicon, is critically dependent on the local strength and flaw population. Experiments and correlating modeling were used to pursue the root cause
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Wall, Neil J. "Characterisation of multiple concentric vortices in hybrid rocket combustion chambers." Thesis, University of Sheffield, 2013. http://etheses.whiterose.ac.uk/4781/.

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Recent developments in hybrid rocket technology involve producing a coaxial bidirectional vortex flow field through use of tangential oxidiser injection at the base of the combustion chamber. This is found to significantly increase engine performance by providing enhanced thermal transfer at the fuel surface, resulting in increased fuel regression rates in addition to more efficient combustion. The double helical path of the flow results in reduced reactant loss at the chamber outlet whilst confining combustion to a high temperature core region defined by the inner vortex. This also results in
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Masquelet, Matthieu M. "Simulations of a Sub-scale Liquid Rocket Engine: Transient Heat Transfer in a Real Gas Environment." Thesis, Available online, Georgia Institute of Technology, 2006, 2006. http://etd.gatech.edu/theses/available/etd-11102006-082702/.

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Libros sobre el tema "Rocket Combustor"

1

Gordon, Sanford. Finite area combustor theoretical rocket performance. National Aeronautics and Space Administration, 1988.

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Muss, J. A. User's manual for Rocket Combustor Interactive Design (ROCCID) and analysis computer program. The Center, 1991.

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William, Brown. Orbit transfer rocket engine technology program: Enhanced heat transfer combustor technology : final report. NASA-Lewis Research Center, 1991.

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4

Dranovsky, Mark L. Combustion Instabilities in Liquid Rocket Engines. American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/4.866906.

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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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Wang, Zhen-Guo. Internal Combustion Processes of Liquid Rocket Engines. John Wiley & Sons Singapore Pte Ltd, 2016. http://dx.doi.org/10.1002/9781118890035.

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Dranovsky, Mark L. Combustion instabilities in liquid rocket engines: Testing and development practices in Russia. American Institute of Aeronautics and Astronautics, 2007.

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Jankowsky, Robert S. Experimental performance of a high-area-ratio rocket nozzle at high combustion chamber pressure. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1996.

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9

North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Combustion of solid propellants. AGARD, 1991.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Combustion of solid propellants. AGARD, 1991.

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Capítulos de libros sobre el tema "Rocket Combustor"

1

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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2

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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Gafni, Gilad, Alexander Kuznetsov, and Benveniste Natan. "Experimental Investigation of an Aluminized Gel Fuel Ramjet Combustor." In Chemical Rocket Propulsion. Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-27748-6_12.

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Kirchheck, Daniel, Dominik Saile, and Ali Gülhan. "Rocket Wake Flow Interaction Testing in the Hot Plume Testing Facility (HPTF) Cologne." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_9.

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Abstract Rocket wake flows were under investigation within the Collaborative Research Centre SFB/TRR40 since the year 2009. The current paper summarizes the work conducted during its third and final funding period from 2017 to 2020. During that phase, focus was laid on establishing a new test environment at the German Aerospace Center (DLR) Cologne in order to improve the similarity of experimental rocket wake flow–jet interaction testing by utilizing hydrogen–oxygen combustion implemented into the wind tunnel model. The new facility was characterized during tests with the rocket combustor model HOC1 in static environment. The tests were conducted under relevant operating conditions to demonstrate the design’s suitability. During the first wind tunnel tests, interaction of subsonic ambient flow at Mach 0.8 with a hot exhaust jet of approx. 920 K was compared to previously investigated cold plume interaction tests using pressurized air at ambient temperature. The comparison revealed significant differences in the dynamic response of the wake flow field on the different types of exhaust plume simulation.
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Perakis, Nikolaos, and Oskar J. Haidn. "Experimental and Numerical Investigation of CH$$_4$$/O$$_2$$ Rocket Combustors." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_23.

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Abstract The experimental investigation of sub-scale rocket engines gives significant information about the combustion dynamics and wall heat transfer phenomena occurring in full-scale hardware. At the same time, the performed experiments serve as validation test cases for numerical CFD models and for that reason it is vital to obtain accurate experimental data. In the present work, an inverse method is developed able to accurately predict the axial and circumferential heat flux distribution in CH$$_4$$/O$$_2$$ rocket combustors. The obtained profiles are used to deduce information about the injector-injector and injector-flame interactions. Using a 3D CFD simulation of the combustion and heat transfer within a multi-element thrust chamber, the physical phenomena behind the measured heat flux profiles can be inferred. A very good qualitative and quantitative agreement between the experimental measurements and the numerical simulations is achieved.
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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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Traxinger, Christoph, Julian Zips, Christian Stemmer, and Michael Pfitzner. "Numerical Investigation of Injection, Mixing and Combustion in Rocket Engines Under High-Pressure Conditions." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_13.

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Abstract The design and development of future rocket engines severely relies on accurate, efficient and robust numerical tools. Large-Eddy Simulation in combination with high-fidelity thermodynamics and combustion models is a promising candidate for the accurate prediction of the flow field and the investigation and understanding of the on-going processes during mixing and combustion. In the present work, a numerical framework is presented capable of predicting real-gas behavior and nonadiabatic combustion under conditions typically encountered in liquid rocket engines. Results of Large-Eddy Simulations are compared to experimental investigations. Overall, a good agreement is found making the introduced numerical tool suitable for the high-fidelity investigation of high-pressure mixing and combustion.
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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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Cheng, S. I. "L*-Combustion Instability in Solid Propellant Rocket Combustion." In Recent Advances in the Aerospace Sciences. Springer US, 1985. http://dx.doi.org/10.1007/978-1-4684-4298-4_13.

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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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Actas de conferencias sobre el tema "Rocket Combustor"

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TAMURA, HIROSHI, FUMIEI ONO, AKINAGA KUMAKAWA, and NOBUYUKI YATSUYANAGI. "LOX/methane staged combustion rocket combustor investigation." In 23rd Joint Propulsion Conference. American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-1856.

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PRIEM, RICHARD, and KEVIN BREISACHER. "3D rocket combustor acoustics model." In 28th Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-3228.

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Matsuyama, Shingo, Junji Shinjo, and Yasuhiro Mizobuchi. "LES of High-Frequency Combustion Instability in a Rocket Combustor." In 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. American Institute of Aeronautics and Astronautics, 2013. http://dx.doi.org/10.2514/6.2013-564.

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KLEM, MARK, JERRY PIEPER, and RICHARD WALKER. "Combustor design and analysis using the ROCket Combustor InteractiveDesign (ROCCID) Methodology." In 26th Joint Propulsion Conference. American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-2240.

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Greatrix, D., and D. Greatrix. "Transverse vibration and rocket combustor internal ballistics." In 33rd Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-3338.

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Lempke, M., P. Gerlinger, and M. Aigner. "Assumed PDF modeling in rocket combustor simulations." In Progress in Propulsion Physics. EDP Sciences, 2013. http://dx.doi.org/10.1051/eucass/201304569.

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Stowe, R., A. De Champlain, and A. Mayer. "Modelling combustor performance of a ducted rocket." In 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-3728.

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Dasari, Abhinav, and Mirko Gamba. "Characterization of Unsteady Combustion Phenomena in a University Scale Rocket Combustor." In 53rd AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-1155.

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Lemcherfi, Aaron I., Rohan Gejji, Tristan L. Fuller, William E. Anderson, and Carson D. Slabaugh. "Investigation of Combustion Instabilities in a Full Flow Staged Combustion Model Rocket Combustor." In AIAA Propulsion and Energy 2019 Forum. American Institute of Aeronautics and Astronautics, 2019. http://dx.doi.org/10.2514/6.2019-3948.

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Matsuyama, Shingo, Junji Shinjo, Satoru Ogawa, and Yasuhiro Mizobuchi. "LES of High-Frequency Combustion Instability in a Single Element Rocket Combustor." In 50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-1271.

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Informes sobre el tema "Rocket Combustor"

1

Zinn, Ben T., Eugene Lubarsky, and Yedidia Neumeier. Real-Time Control for Optimal Liquid Rocket Combustor Performance. Defense Technical Information Center, 2005. http://dx.doi.org/10.21236/ada443134.

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Jenkins, R. A., C. W. Nestor, C. V. Thompson, et al. Characterization of rocket propellant combustion products. Office of Scientific and Technical Information (OSTI), 1991. http://dx.doi.org/10.2172/5712917.

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Williams, Forman A. Fundamental Studies of Liquid-Propellant Rocket Combustion. Defense Technical Information Center, 2004. http://dx.doi.org/10.21236/ada425218.

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Anderson, William E., Stephen D. Heister, and Steven S. Son. Fuel Chemistry And Combustion Distribution Effects On Rocket Engine Combustion Stability. Defense Technical Information Center, 2015. http://dx.doi.org/10.21236/ad1001343.

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Anderson, William E., Stephen D. Heister, and Steven S. Son. Fuel Chemistry And Combustion Distribution Effects On Rocket Engine Combustion Stability. Defense Technical Information Center, 2013. http://dx.doi.org/10.21236/ada577052.

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Anderson, William E., Steven F. Son, and Stephen D. Heister. Fuel Chemistry and Combustion Distribution Effects on Rocket Engine Combustion Stability. Defense Technical Information Center, 2012. http://dx.doi.org/10.21236/ada566310.

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Price, E. W., and G. A. Flandro. Combustion Instability in Solid Propellant Rockets. Defense Technical Information Center, 1987. http://dx.doi.org/10.21236/ada179701.

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Gundersen, Martin A. Plasma-Enhanced Combustion for Reduction of Rocket Plume Soot. Defense Technical Information Center, 2001. http://dx.doi.org/10.21236/ada397824.

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Williams, Forman A. Combustion Processes and Instabilities in Liquid-Propellant Rocket Engines. Defense Technical Information Center, 2004. http://dx.doi.org/10.21236/ada420091.

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Jenkins, R. A. Characterization of rocket propellant combustion products: Description of sampling and analysis methods for rocket exhaust characterization studies. Office of Scientific and Technical Information (OSTI), 1990. http://dx.doi.org/10.2172/6524606.

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