Добірка наукової літератури з теми "Rocket engines – Combustion – Mathematical models"
Оформте джерело за APA, MLA, Chicago, Harvard та іншими стилями
Ознайомтеся зі списками актуальних статей, книг, дисертацій, тез та інших наукових джерел на тему "Rocket engines – Combustion – Mathematical models".
Біля кожної праці в переліку літератури доступна кнопка «Додати до бібліографії». Скористайтеся нею – і ми автоматично оформимо бібліографічне посилання на обрану працю в потрібному вам стилі цитування: APA, MLA, «Гарвард», «Чикаго», «Ванкувер» тощо.
Також ви можете завантажити повний текст наукової публікації у форматі «.pdf» та прочитати онлайн анотацію до роботи, якщо відповідні параметри наявні в метаданих.
Статті в журналах з теми "Rocket engines – Combustion – Mathematical models"
Sidlerov, D. A., and S. A. Fedorov. "Numerical Investigation of Work Cycle Characteristics in the Combustion Chamber of a Lox/Methane Liquid-Propellant Rocket Engine Featuring Reductant Power Gas Combustion." Herald of the Bauman Moscow State Technical University. Series Mechanical Engineering, no. 2 (141) (June 2022): 43–53. http://dx.doi.org/10.18698/0236-3941-2022-2-43-53.
Повний текст джерелаChernova, A. A. "Validation of RANS Turbulence Models for the Conjugate Heat Exchange Problem." Nelineinaya Dinamika 18, no. 1 (2022): 61–82. http://dx.doi.org/10.20537/nd220105.
Повний текст джерелаGorskiy, V. V., M. G. Kovalsky, and V. G. Resh. "Method of Calculating Carbon Ablation in the Jet of Liquid Rocket Engine Combustion Products." Herald of the Bauman Moscow State Technical University. Series Mechanical Engineering, no. 5 (128) (October 2019): 4–21. http://dx.doi.org/10.18698/0236-3941-2019-5-4-21.
Повний текст джерелаRamesh, Davood, Hasan Karimi M., and Massoud Shahheidari. "Cycle optimization of the staged combustion rocket engines." Aircraft Engineering and Aerospace Technology 89, no. 2 (March 6, 2017): 304–13. http://dx.doi.org/10.1108/aeat-12-2013-0229.
Повний текст джерелаBetelin, V. B., R. M. Shagaliev, S. V. Aksenov, I. M. Belyakov, Yu N. Deryuguin, D. A. Korchazhkin, A. S. Kozelkov, V. F. Nikitin, A. V. Sarazov, and D. K. Zelenskiy. "Mathematical simulation of hydrogen–oxygen combustion in rocket engines using LOGOS code." Acta Astronautica 96 (March 2014): 53–64. http://dx.doi.org/10.1016/j.actaastro.2013.11.008.
Повний текст джерелаONEL, Alexandru-Iulian, Oana-Iuliana POPESCU, Ana-Maria NECULAESCU, Tudorel-Petronel AFILIPOAE, and Teodor-Viorel CHELARU. "Liquid rocket engine performance assessment in the context of small launcher optimisation." INCAS BULLETIN 11, no. 3 (September 9, 2019): 135–45. http://dx.doi.org/10.13111/2066-8201.2019.11.3.12.
Повний текст джерелаVasiliev, Igor, Boris Kiforenko, and Yaroslav Tkachenko. "COMPARATIVE ANALYSIS OF THE EFFICIENCY OF CONSTANT POWER THROTTLED ROCKET ENGINES FOR INTERORBITAL FLIGHTS TO GEOSTATIONAR." Journal of Automation and Information sciences 6 (November 1, 2021): 66–77. http://dx.doi.org/10.34229/1028-0979-2021-6-7.
Повний текст джерелаStrelnikov, G. A., A. D. Yhnatev, N. S. Pryadko, and S. S. Vasyliv. "Gas flow control in rocket engines." Technical mechanics 2021, no. 2 (June 29, 2021): 60–77. http://dx.doi.org/10.15407/itm2021.02.060.
Повний текст джерелаVaulin, S. D., and K. I. Khazhiakhmetov. "The State-of-the-Art and Prospects of Aerospike Engines." Proceedings of Higher Educational Institutions. Маchine Building, no. 10 (739) (October 2021): 74–83. http://dx.doi.org/10.18698/0536-1044-2021-10-74-83.
Повний текст джерелаPylypenko, O. V., O. O. Prokopchuk, S. I. Dolgopolov, O. D. Nikolayev, N. V. Khoriak, V. Yu Pysarenko, I. D. Bashliy, and S. V. Polskykh. "Mathematical modelling of start-up transients at clustered propulsion system with POGO-suppressors for CYCLON-4M launch vehicle." Kosmìčna nauka ì tehnologìâ 27, no. 6 (2021): 3–15. http://dx.doi.org/10.15407/knit2021.06.003.
Повний текст джерелаДисертації з теми "Rocket engines – Combustion – Mathematical models"
Sone, Kazuo. "Unsteady simulations of mixing and combustion in internal combustion engines." Thesis, Georgia Institute of Technology, 2001. http://hdl.handle.net/1853/12171.
Повний текст джерелаLaurent, Charlelie. "Low-order modeling and high-fidelity simulations for the prediction of combustion instabilities in liquid rocket engines and gas turbines." Thesis, Toulouse, INPT, 2020. http://www.theses.fr/2020INPT0038.
Повний текст джерелаOver the last decades, combustion instabilities have been a major concern for a number of industrial projects, especially in the design of Liquid Rocket Engines (LREs) and gas turbines. Mitigating their effects requires a solid scientific understanding of the intricate interplay between flame dynamics and acoustic waves that they involve. During this PhD work, several directions were explored to provide a better comprehension of flame dynamics in cryogenic rocket engines, as well as more efficient and robust numerical methods for the prediction of thermoacoustic instabilities in complex combustors. The first facet of this work consisted in the resolution of unstable thermoacoustic modes in complex multi-injectors combustors, a task that often requires a number of simplifications to be computationally affordable. These necessary physics-based assumptions led to the growing popularity of acoustic Low-Order Models (LOMs), among which Galerkin expansion LOMs have displayed a promising efficiency while retaining a satisfactory accuracy. Those are however limited to simple geometries that do not incorporate the complex features of industrial systems. A major part of this work therefore consisted first in clearly identifying the mathematical limitations of the classical Galerkin expansion, and then in designing a novel type of modal expansion, named a frame expansion, that does not suffer from the same restrictions. In particular, the frame expansion is able to accurately represent the acoustic velocity field, near non-rigid-wall boundaries of the combustor, a crucial ability that the Galerkin method lacks. In this work, the concept of surface modal expansion is also introduced to model topologically complex boundaries, such as multi-perforated liners encountered in gas turbines. These novel numerical methods were combined with the state-space formalism to build acoustic networks of complex systems. The resulting LOM framework was implemented in the code STORM (State-space Thermoacoustic low-ORder Model), which enables the low-order modeling of thermoacoustic instabilities in arbitrarily complex geometries. The second ingredient in the prediction of thermoacoustic instabilities is the flame dynamics modeling. This work dealt with this problem, in the specific case of a cryogenic coaxial jet-flame characteristic of a LRE. Flame dynamics driving phenomena were identified thanks to three-dimensional Large Eddy Simulations (LES) of the Mascotte experimental test rig where both reactants (CH4 and O2) are injected in transcritical conditions. A first simulation provides a detailed insight into the flame intrinsic dynamics. Several LES with harmonic modulation of the fuel inflow at various frequencies and amplitudes were performed in order to evaluate the flame response to acoustic oscillations and compute a Flame Transfer Function (FTF). The flame nonlinear response, including interactions between intrinsic and forced oscillations, were also investigated. Finally, the stabilization of this flame in the near-injector region, which is of primary importance on the overall flame dynamics, was investigated thanks to muulti-physics two-dimensional Direct Numerical Simulations (DNS), where a conjugate heat transfer problem is resolved at the injector lip
Cordesse, Pierre. "Contribution to the study of combustion instabilities in cryotechnic rocket engines : coupling diffuse interface models with kinetic-based moment methods for primary atomization simulations." Thesis, université Paris-Saclay, 2020. http://www.theses.fr/2020UPASC016.
Повний текст джерелаGatekeepers to the open space, launchers are subject to intense and competitive enhancements, through experimental and numerical test campaigns. Predictive numerical simulations have become mandatory to increase our understanding of the physics. Adjustable, they provide early-stage optimization processes, in particular of the combustion chamber, to guaranty safety and maximize efficiency. One of the major physical phenomenon involved in the combustion of the fuel and oxidizer is the jet atomization, which pilotes both the droplet distributions and the potential high-frequency instabilities in subcritical conditions. It encompasses a large sprectrum of two-phase flow topologies, from separated phases to disperse phase, with a mixed region where the small scale physics and topology of the flow are very complex. Reduced-order models are good candidates to perform predictive but low CPU demanding simulations on industrial configurations but have only been able so far to capture large scale dynamics and have to be coupled to disperse phase models through adjustable and weakly reliable parameters in order to predict spray formation. Improving the hierarchy of reduced order models in order to better describe both the mixed region and the disperse region requires a series of building blocks at the heart of the present work and give on to complex problems in the mathematical analysis and physical modelling of these systems of PDE as well as their numerical discretization and implementation in CFD codes for industrial uses. Thanks to the extension of the theory on supplementary conservative equations to system of non-conservation laws and the formalism of the multi-fluid thermodynamics accounting for non-ideal effects, we give some new leads to define a strictly convex mixture entropy consistent with the system of equations and the pressure laws, which would allow to recover the entropic symmetrization of two-phase flow models, prove their hyperbolicity and obtain generalized source terms. Furthermore, we have departed from a geometric approach of the interface and proposed a multi-scale rendering of the interface to describe multi-fluid flow with complex interface dynamics. The Stationary Action Principle has returned a single velocity two-phase flow model coupling large and small scales of the flow. We then have developed a splitting strategy based on a Finite Volume discretization and have implemented the new model in the industrial CFD software CEDRE of ONERA to proceed to a numerical verification. Finally, we have constituted and investigated a first building block of a hierarchy of test-cases designed to be amenable to DNS while close enough to industrial configurations in order to assess the simulation results of the new model but also to any up-coming models
Sullwald, Wichard. "Grain regression analysis." Thesis, Stellenbosch : Stellenbosch University, 2014. http://hdl.handle.net/10019.1/86526.
Повний текст джерелаENGLISH ABSTRACT: Grain regression analysis forms an essential part of solid rocket motor simulation. In this thesis a numerical grain regression analysis module is developed as an alternative to cumbersome and time consuming analytical methods. The surface regression is performed by the level-set method, a numerical interface advancement scheme. A novel approach to the integration of the surface area and volume of a numerical interface, as defined implicitly in a level-set framework, by means of Monte-Carlo integration is proposed. The grain regression module is directly coupled to a quasi -1D internal ballistics solver in an on-line fashion, in order to take into account the effects of spatially varying burn rate distributions. A multi-timescale approach is proposed for the direct coupling of the two solvers.
AFRIKAANSE OPSOMMING: Gryn regressie analise vorm ’n integrale deel van soliede vuurpylmotor simulasie. In hierdie tesis word ’n numeriese gryn regressie analise model, as ’n alternatief tot dikwels omslagtige en tydrowende analitiese metodes, ontwikkel. Die oppervlak regressie word deur die vlak-set metode, ’n numeriese koppelvlak beweging skema uitgevoer. ’n Nuwe benadering tot die integrasie van die buite-oppervlakte en volume van ’n implisiete numeriese koppelvlak in ’n vlakset raamwerk, deur middel van Monte Carlo-integrasie word voorgestel. Die gryn regressie model word direk en aanlyn aan ’n kwasi-1D interne ballistiek model gekoppel, ten einde die uitwerking van ruimtelik-wisselende brand-koers in ag te neem. ’n Multi-tydskaal benadering word voorgestel vir die direkte koppeling van die twee modelle.
Deng, Tian. "LES combined with statistical models of spray formation closely to air-blast atomizer." Thesis, Ecully, Ecole centrale de Lyon, 2011. http://www.theses.fr/2011ECDL0037/document.
Повний текст джерелаThis thesis introduced an extension to stochastic approach for simulation of air-blast atomization closely to injector. This approach was previously proposed in publications of Gorokhovski with his PHD students. Our extension of this approach is as follows. In the framework of LES approach, the contribution of primary atomization zone is simulated as an immersed solid body with stochastic structure. The last one is defined by stochastic simulation of position-and-curvature of interface between the liquid and the gas. As it was done previously in this approach, the simulation of the interface position was based on statistical universalities of fragmentation under scaling symmetry. Additionally to this, we simulate the outwards normal to the interface, assuming its stochastic relaxation to isotropy along with propagation of spray in the down-stream direction. In this approach, the statistics of immersed body force plays role of boundary condition for LES velocity field, as well as for production of primary blobs, which are then tracked in the Lagrangian way. In this thesis, the inter-particle collisions in the primary atomisation zone are accounted also by analogy with standard kinetic approach for the ideal gas. The closure is proposed for the statistical temperature of droplets. The approach was assessed by comparison with measurements of Hong in his PHD. The results of computation showed that predicted statistics of the velocity and of the size in the spray at different distances from the center plane, at different distances from the nozzle orifice, at different inlet conditions (different gas velocity at constant gas-to-liquid momentum ratio, different gas-to-liquid momentum ratio) are relatively close to measurements. Besides, the specific role of recirculation zone in front of the liquid core was emphasized in the flapping of the liquid core and in the droplets production
Nahorniak, Matthew T. "Feasibility of Lorentz mixing to enhance combustion in supersonic diffusion flames." Thesis, 1996. http://hdl.handle.net/1957/34208.
Повний текст джерелаGraduation date: 1997
Hansen, Alan Christopher. "A diagnostic quasi-dimensional model of heat transfer and combustion in compression-ignition engines." Thesis, 1989. http://hdl.handle.net/10413/9595.
Повний текст джерелаThesis (Ph.D.)-University of Natal, Pietermaritzburg, 1989.
"A Numerical Study of a Rotary Valve Internal Combustion Engine." University of Technology, Sydney. Faculty of Engineering, 2001. http://hdl.handle.net/2100/248.
Повний текст джерелаEkici, Özgür 1973. "Computational study of arc discharges : spark plug and railplug ignitors [sic]." 2007. http://hdl.handle.net/2152/11950.
Повний текст джерелаFitzpatrick, John Nathan. "Coupled thermal-fluid analysis with flowpath-cavity interaction in a gas turbine engine." Thesis, 2013. http://hdl.handle.net/1805/4441.
Повний текст джерелаThis study seeks to improve the understanding of inlet conditions of a large rotor-stator cavity in a turbofan engine, often referred to as the drive cone cavity (DCC). The inlet flow is better understood through a higher fidelity computational fluid dynamics (CFD) modeling of the inlet to the cavity, and a coupled finite element (FE) thermal to CFD fluid analysis of the cavity in order to accurately predict engine component temperatures. Accurately predicting temperature distribution in the cavity is important because temperatures directly affect the material properties including Young's modulus, yield strength, fatigue strength, creep properties. All of these properties directly affect the life of critical engine components. In addition, temperatures cause thermal expansion which changes clearances and in turn affects engine efficiency. The DCC is fed from the last stage of the high pressure compressor. One of its primary functions is to purge the air over the rotor wall to prevent it from overheating. Aero-thermal conditions within the DCC cavity are particularly challenging to predict due to the complex air flow and high heat transfer in the rotating component. Thus, in order to accurately predict metal temperatures a two-way coupled CFD-FE analysis is needed. Historically, when the cavity airflow is modeled for engine design purposes, the inlet condition has been over-simplified for the CFD analysis which impacts the results, particularly in the region around the compressor disc rim. The inlet is typically simplified by circumferentially averaging the velocity field at the inlet to the cavity which removes the effect of pressure wakes from the upstream rotor blades. The way in which these non-axisymmetric flow characteristics affect metal temperatures is not well understood. In addition, a constant air temperature scaled from a previous analysis is used as the simplified cavity inlet air temperature. Therefore, the objectives of this study are: (a) model the DCC cavity with a more physically representative inlet condition while coupling the solid thermal analysis and compressible air flow analysis that includes the fluid velocity, pressure, and temperature fields; (b) run a coupled analysis whose boundary conditions come from computational models, rather than thermocouple data; (c) validate the model using available experimental data; and (d) based on the validation, determine if the model can be used to predict air inlet and metal temperatures for new engine geometries. Verification with experimental results showed that the coupled analysis with the 3D no-bolt CFD model with predictive boundary conditions, over-predicted the HP6 offtake temperature by 16k. The maximum error was an over-prediction of 50k while the average error was 17k. The predictive model with 3D bolts also predicted cavity temperatures with an average error of 17k. For the two CFD models with predicted boundary conditions, the case without bolts performed better than the case with bolts. This is due to the flow errors caused by placing stationary bolts in a rotating reference frame. Therefore it is recommended that this type of analysis only be attempted for drive cone cavities with no bolts or shielded bolts.
Книги з теми "Rocket engines – Combustion – Mathematical models"
Etele, Jason. Computational study of variable area ejector rocket flowfields. [Downsview, Ont: University of Toronto, Institute for Aerospace Studies], 2004.
Знайти повний текст джерелаYe ti huo jian fa dong ji ran shao guo cheng jian mo yu shu zhi fang zhen: Modeling and numerical simulations of internal combustion process of liquid rocket engines. Beijing: Guo fang gong ye chu ban she, 2012.
Знайти повний текст джерелаRocker, M. Modeling on nonacoustic combustion instability in simulations of hybrid motor tests. Marshall Space Flight Center, Ala: National Aeronautics and Space Administration, Marshall Space Flight Center, 2000.
Знайти повний текст джерелаYe ti huo jian fa dong ji ran shao dong li xue mo xing yu shu zhi ji suan. Beijing Shi: Guo fang gong ye chu ban she, 2011.
Знайти повний текст джерелаShi, Yu. Computational optimization of internal combustion engines. London: Springer, 2011.
Знайти повний текст джерелаRamos, J. I. Internal combustion engine modeling. New York: Hemisphere Pub. Corp., 1989.
Знайти повний текст джерелаZeleznik, Frank J. Modeling the internal combustion engine. Washington, D.C: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1985.
Знайти повний текст джерелаZeleznik, Frank J. Modeling the internal combustion engine. Washington, D.C: NASA, 1985.
Знайти повний текст джерелаModeling of combustion systems: A practical approach. Boca Raton, FL: CRC Press, 2006.
Знайти повний текст джерелаGerke, Udo. Numerical analysis of mixture formation and combustion in a hydrogen direct-injection internal combustion engine. Göttingen: Cuvillier, 2007.
Знайти повний текст джерелаЧастини книг з теми "Rocket engines – Combustion – Mathematical models"
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, 209–21. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_13.
Повний текст джерелаPerakis, 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, 359–79. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_23.
Повний текст джерелаPearson, Ronald K. "Motivations and Perspectives." In Discrete-time Dynamic Models. Oxford University Press, 1999. http://dx.doi.org/10.1093/oso/9780195121988.003.0003.
Повний текст джерелаТези доповідей конференцій з теми "Rocket engines – Combustion – Mathematical models"
Ferrero, Andrea, Filippo Masseni, and Dario Pastrone. "Low-order models for low-frequency combustion instability in hybrid rocket engines." In INTERNATIONAL CONFERENCE OF NUMERICAL ANALYSIS AND APPLIED MATHEMATICS ICNAAM 2019. AIP Publishing, 2020. http://dx.doi.org/10.1063/5.0026694.
Повний текст джерелаGuo, J., Y. P. Cao, W. P. Zhang, and X. Y. Zhang. "A New Numerical Method for Developing the Lumped Dynamic Model of Valve Train." In ASME 2014 Internal Combustion Engine Division Fall Technical Conference. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/icef2014-5530.
Повний текст джерелаCoclite, Alessandro, Luigi Cutrone, Giuseppe Pascazio, and Pietro De Palma. "Numerical investigation of high-pressure combustion in rocket engines using Flamelet/Progress-variable models." In 53rd AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-1109.
Повний текст джерелаDanov, Stanislav N., and Ashwani K. Gupta. "Influence of Imperfections in the Working Media on Diesel Engine Indicator Process: Part 2 — Results." In ASME 1998 Design Engineering Technical Conferences. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/detc98/cie-6027.
Повний текст джерелаDanov, Stanislav N., and Ashwani K. Gupta. "Influence of Imperfections in Working Media on Diesel Engine Indicator Process: Part 1 — Theory." In ASME 1998 Design Engineering Technical Conferences. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/detc98/cie-6026.
Повний текст джерелаLanzafame, R., and M. Messina. "Fuels Characterization for Use in Internal Combustion Engines." In ASME 2001 Internal Combustion Engine Division Fall Technical Conference. American Society of Mechanical Engineers, 2001. http://dx.doi.org/10.1115/2001-ice-421.
Повний текст джерелаBenelli, G., L. Carrai, S. Sigali, I. Brunetti, and L. Castellano. "Thermoacoustic Models for Evaluating the Sensitivity to Instabilities of Multi-Burner Annular Combustion Chambers." In ASME Turbo Expo 2008: Power for Land, Sea, and Air. ASMEDC, 2008. http://dx.doi.org/10.1115/gt2008-51246.
Повний текст джерелаDe Giorgi, Maria Grazia, Aldebara Sciolti, and Antonio Ficarella. "Spray and Combustion Modeling in High Pressure Cryogenic Jet Flames." In ASME Turbo Expo 2012: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/gt2012-69544.
Повний текст джерелаBorissov, Anatoli, and James J. McCoy. "Supersonic Injection of Gaseous Fuel Described as Possible Solution for NOx Emissions From Large-Bore Gas Engines." In ASME 2002 Internal Combustion Engine Division Spring Technical Conference. ASMEDC, 2002. http://dx.doi.org/10.1115/ices2002-448.
Повний текст джерелаBrusca, S., S. Collura, R. Lanzafame, and M. Messina. "The Influence of Specific Heats Variability on Heat Release Analysis Using Two-Zone Models." In ASME 2006 International Mechanical Engineering Congress and Exposition. ASMEDC, 2006. http://dx.doi.org/10.1115/imece2006-13456.
Повний текст джерела