Tesis sobre el tema "Scramjet engine"
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Barone, Dominic L. "Investigation of TDLAS Measurements in a Scramjet Engine". University of Cincinnati / OhioLINK, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1277130335.
Texto completoZinnecker, Alicia M. "Modeling for Control Design of an Axisymmetric Scramjet Engine Isolator". The Ohio State University, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=osu1354215841.
Texto completoMcGillivray, Nathan T. "Coupling Computational Fluid Dynamics Analysis and Optimization Techniques for Scramjet Engine Design". Wright State University / OhioLINK, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=wright1536311445147862.
Texto completoEugênio, Ribeiro Fábio Henrique. "Numerical Simulation of Turbulent Combustion in Situations Relevant to Scramjet Engine Propulsion". Thesis, Chasseneuil-du-Poitou, Ecole nationale supérieure de mécanique et d'aérotechnique, 2019. http://www.theses.fr/2019ESMA0001/document.
Texto completoScramjet engines are high-speed air breathing propulsion systems that do not require rotating elements to compress the air inlet stream. The flow is compressed dynamically through a supersonic intake system integrated in the aircraft’s forebody, reaching the required pressure and temperature for combustion to proceed within the combustor in this kind of engine. The combustion chamber is crossed by a supersonic flow, which limits severely the time available to inject fuel, mix it with oxidizer, ignite the resulting mixture and reach complete combustion. Cavities can be used to increase the residence time without excessive total pressure loss and are therefore used as flame holders in supersonic combustors.This thesis focuses in studying the flame stabilization mechanism and turbulence-chemistry interactions for a jet in a supersonic crossflow (JISCF) of vitiated air with hydrogen injection upstream of a wall-mounted squared cavity. The corresponding reactive high-speed flow conditions are scrutinized on the basis of numerical simulations of a scramjet model representative of experiments previously conducted at the University of Michigan. The computations are performed with the high-performance computational solver CREAMS, developed to perform the numerical simulation of compressible reactive multi-component flows on massively-parallel architectures. The solver makes use of high-order precision numerical schemes applied on structured meshes and the combustion chamber geometry is modeled by using the Immersed Boundary Method (IBM) algorithm. The present set of computations is conducted within the LES framework and the subgrid viscosity is treated with the wall-adapting local eddy (WALE)model. Two distinct temperatures are considered in the inlet vitiated airstream to study combustion stabilization. Special emphasis is placed on the analysis of the reactive flow topology and structure,and the combustion regimes are analyzed on the basis of standard turbulent combustion diagrams
Maddalena, Luca. "Investigations of Injectors for Scramjet Engines". Diss., Virginia Tech, 2007. http://hdl.handle.net/10919/28683.
Texto completoPh. D.
Miki, Kenji. "Simulation of magnetohydrodynamics turbulence with application to plasma-assisted supersonic combustion". Diss., Atlanta, Ga. : Georgia Institute of Technology, 2009. http://hdl.handle.net/1853/26605.
Texto completoCommittee Chair: Menon Suresh; Committee Co-Chair: Jagoda Jeff; Committee Member: Ruffin Stephen; Committee Member: Thorsten Stoesser; Committee Member: Walker Mitchell. Part of the SMARTech Electronic Thesis and Dissertation Collection.
Fischer, Christian Max [Verfasser]. "Investigation of the isolator flow of scramjet engines / Christian Max Fischer". Aachen : Hochschulbibliothek der Rheinisch-Westfälischen Technischen Hochschule Aachen, 2014. http://d-nb.info/1059796627/34.
Texto completoCocks, Peter. "Large eddy simulation of supersonic combustion with application to scramjet engines". Thesis, University of Cambridge, 2011. https://www.repository.cam.ac.uk/handle/1810/239344.
Texto completoMoura, Augusto Fontan. "A computational study of the airflow at the intake region of scramjet engines". Instituto Tecnológico de Aeronáutica, 2014. http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=2973.
Texto completoNajafiyazdi, Alireza. "Theoretical and numerical analysis of supersonic inlet starting by mass spillage". Thesis, McGill University, 2007. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=111524.
Texto completoThe theory involves three parameters to incorporate the multi-dimensional nature of mass spillage through a wall perforation. Mass spillage through an individual slot is studied to determine these parameters; analytical expressions for these parameters are derived for both subsonic and supersonic flow conditions. In the case of mass spillage from supersonic flows, the relations are exact. However, due to the complexity of flow field, the theory is an approximation for subsonic flows. Therefore, a correction factor is introduced which is determined from an empirical relation obtained from numerical simulations.
A methodology is also proposed to determine perforation size and distribution to achieve flow starting for a given inlet at a desired free-stream Mach number. The problem of shock stability inside a perforated inlet designed with the proposed method is also discussed.
The method is demonstrated for some test cases. Time-realistic CFD simulations and experimental results in the literature confirm the accuracy of the theory and the reliability of the proposed design methodology.
Yanson, Logan M. "Effects of Liquid Superheat on Droplet Disruption in a Supersonic Stream". Link to electronic thesis, 2005. http://www.wpi.edu/Pubs/ETD/Available/etd-042905-151247/.
Texto completoDel, Rio Francesco. "Distortion mechanism in supersonic combustion ramjet engines". Master's thesis, Alma Mater Studiorum - Università di Bologna, 2018.
Buscar texto completoMalo-Molina, Faure Joel. "Numerical study of innovative scramjet inlets coupled to combustors using hydrocarbon-air mixture". Diss., Georgia Institute of Technology, 2010. http://hdl.handle.net/1853/33906.
Texto completoAxdahl, Erik Lee. "A study of premixed, shock-induced combustion with application to hypervelocity flight". Diss., Georgia Institute of Technology, 2013. http://hdl.handle.net/1853/50290.
Texto completoO'Byrne, Sean Brendan. "Examination of transient mixing and combustion processes in a supersonic combustion ramjet engine". Master's thesis, 1997. http://hdl.handle.net/1885/145993.
Texto completoCheng, Chun-Chang y 陳均彰. "Mixing Analysis of a Scramjet engine via DSMC method". Thesis, 2012. http://ndltd.ncl.edu.tw/handle/41993388924996868161.
Texto completo淡江大學
機械與機電工程學系碩士班
100
Supersonic combustion ramjet engine work flow field are thin. Therefore, We have to use micro particle to analyze. The macro continuum hypothesis is no longer suitable. This article use one of the Numerical Solution to simulate DSMC. It is precise and used a lot of analyze recently. This article adopted the variety of Scramjet inner flow field by DSMC. We consider the situation of fuel ignition and air mixing. How to achieve good mixing efficiency has become concerned about the direction of the research, therefore, for a variety of different the combustion chamber configuration calculation and analysis its mixing efficiency.
Hima, Bindu V. "Experimental Investigations Of Aerothermodynamics Of A Scramjet Engine Configuration". Thesis, 2009. https://etd.iisc.ac.in/handle/2005/1120.
Texto completoHima, Bindu V. "Experimental Investigations Of Aerothermodynamics Of A Scramjet Engine Configuration". Thesis, 2009. http://hdl.handle.net/2005/1120.
Texto completo謝宗燁. "Study of Combustion Effects for Hydrogen Injection in Scramjet Engine Combustor". Thesis, 2015. http://ndltd.ncl.edu.tw/handle/89420493458057462392.
Texto completo逢甲大學
航太與系統工程學系
103
This study describes using the finite volume method to solve Reynold average Navier-Stokes Equations, in order to simulates the flow field of external intake compression ramp to the internal combustion chamber on a supersonic combustion ramjet engine(Scramjet Engine). And this thesis uses non-premixed combustion model to simulate the combustion reaction process of supersonic combustion. The operation theory of supersonic combustion ramjet engine is that in hypersonic flight conditions, air compressed by shock waves pass into the combustion chamber and produce combustion reaction with fuel. The flow through nozzle exchange for thrust at last. This research focuses on the phenomena of heat flow in the combustion chamber when the fluid combusts in the supersonic conditions. Previous study observes the sequence of external shock wave development through two dimension unsteady simulations with non-fuel injection. After that, the research observes the influence of Hydrogen injection velocity interact the combustion field by maintaining the total pressure and total temperature of fuel and changing the injection mach number to 2.5, 2.75, 3.0. This study discovers injection speed influence the deflection angle of shock wave. It indirectly affects times of shock reflection and merged position on the wall. The injection velocity also affects the thickness of the flame. Hydrogen injects more faster, the flame thickness become thinner. The research further explores a three-dimensional combustion chamber, and uses unsteady simulation to observe the shape of flame in the three-dimensional supersonic combustion flow field. Then we acquire the combustion phenomena of profile section through the presentation of streamlines for the combustion chamber along the axial channel. This research discovers the supersonic combustion flow patterns closely linked with shock waves reflection and intersection.
Wang, Chen-Yen y 王鎮彥. "Three-dimensional inflow Analysis of a Scramjet engine via DSMC method". Thesis, 2013. http://ndltd.ncl.edu.tw/handle/42813589651468571601.
Texto completo淡江大學
機械與機電工程學系碩士班
101
In this study, the direct simulation Monte Carlo method was used in simulating the internal flow field and fuel mixing efficiency of a three-dimensional supersonic combustion ramjet (scramjet) engine to investigate the changes in the internal field of air inlets at varying Mach numbers and for different physical appearances. The study results show that oblique shock waves and normal shock waves affect the mixing quality of hydrogen in the combustion chamber. The simulated air inlet conditions were 12, 15, and 18 Mach. In addition, two types of physical appearances were tested, specifically, concave cavity and rear-ramped concave cavity. By comparing the results obtained from the three-dimensional simulations with extant two-dimensional simulation results, this study endeavors to increase simulation accuracy. These comparative results can then be used as a reference for conducting major simulations in the future.
Rodrigues, Luís. "Thermodynamic analysis and optimization of a scramjet engine with thermal management system". Master's thesis, 2010. http://hdl.handle.net/10400.6/3686.
Texto completoRoberts, Kristen Nicole. "Analysis and design of a hypersonic scramjet engine with a starting mach number of 4.00". 2008. http://hdl.handle.net/10106/1073.
Texto completoCassone, Egidio. "Combustion processes modeling: numerical investigations of an engine equipped with a Turbulent Jet Ignition system and of a scramjet combustor". Doctoral thesis, 2022. http://hdl.handle.net/11589/240300.
Texto completoDevaraj, Manoj Kumar K. "Physical insights into unstart dynamics of a hypersonic mixed compression intake". Thesis, 2021. https://etd.iisc.ac.in/handle/2005/5655.
Texto completoWilliams, Nehemiah Joel. "A Performance Analysis of a Rocket Based Combined Cycle (RBCC) Propulsion System for Single-Stage-To-Orbit Vehicle Applications". 2010. http://trace.tennessee.edu/utk_gradthes/842.
Texto completoKoo, Heeseok. "Large-eddy simulations of scramjet engines". Thesis, 2011. http://hdl.handle.net/2152/ETD-UT-2011-05-3203.
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(6632393), Ian Avalon Hall. "Simulating Scramjet Behavior: Unstart Prediction in a Supersonic, Turbulent Inlet-Isolator Duct Flow". Thesis, 2019.
Buscar texto completoPulford, David Robert Newman. "Coherent anti-Stokes Raman scattering in a free piston shock tunnel". Phd thesis, 1994. http://hdl.handle.net/1885/138398.
Texto completoNahorniak, Matthew T. "Feasibility of Lorentz mixing to enhance combustion in supersonic diffusion flames". Thesis, 1996. http://hdl.handle.net/1957/34208.
Texto completoGraduation date: 1997
Mahapatra, Debabrata. "Investigation Of Ramp/Cowl Shock Interaction Processes Near A Generic Scramjet Inlet At Hypersonic Mach Number". Thesis, 2008. https://etd.iisc.ac.in/handle/2005/807.
Texto completoMahapatra, Debabrata. "Investigation Of Ramp/Cowl Shock Interaction Processes Near A Generic Scramjet Inlet At Hypersonic Mach Number". Thesis, 2008. http://hdl.handle.net/2005/807.
Texto completoChakraborty, Debasis. "Confined Reacting Supersonic Mixing Layer - A DNS Study With Analysis Of Turbulence And Combustion Models". Thesis, 1998. https://etd.iisc.ac.in/handle/2005/2167.
Texto completoChakraborty, Debasis. "Confined Reacting Supersonic Mixing Layer - A DNS Study With Analysis Of Turbulence And Combustion Models". Thesis, 1998. http://etd.iisc.ernet.in/handle/2005/2167.
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