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Artykuły w czasopismach na temat "Tuyère supersonique"
Mahfoudi, El-Ahcene, Abderrahmane Gahmousse, Athmane Harizi, Kamel Talbi i Abdellah Hadjadj. "Simulation numérique de l’écoulement compressible supersonique Application aux tuyères propulsives à combustible liquide hydrogène". Journal of Renewable Energies 15, nr 3 (23.10.2023): 365–72. http://dx.doi.org/10.54966/jreen.v15i3.327.
Pełny tekst źródłaMahfoudi, El-Ahcene, Abderrahmane Gahmousse i Kamel Talbi. "Etude numérique de l’écoulement compressible turbulent dans une tuyère supersonique". Journal of Renewable Energies 16, nr 2 (22.10.2023). http://dx.doi.org/10.54966/jreen.v16i2.380.
Pełny tekst źródłaRozprawy doktorskie na temat "Tuyère supersonique"
Mangin, Bruno. "Vectorisation fluidique de la poussée d'une tuyère plane supersonique". Orléans, 2006. http://www.theses.fr/2006ORLE2046.
Pełny tekst źródłaGirard, Stève. "Etude des charges latérales dans une tuyère supersonique surdétendue". Poitiers, 1999. http://www.theses.fr/1999POIT2373.
Pełny tekst źródłaBourgoing, Alexis. "Instationnarité et dissymétrie d'un écoulement supersonique décollé dans une tuyère plane". Phd thesis, Université Pierre et Marie Curie - Paris VI, 2002. http://tel.archives-ouvertes.fr/tel-00003256.
Pełny tekst źródłaDes simulations numériques bidimensionnelles et stationnaires réalisées en régime turbulent ont permis de confronter les modèles de turbulence les plus employés. Les résultats montrent des configurations de chocs différentes suivant les modèles adoptés. Une configuration dissymétrique a été obtenue par la simulation du transitoire d'amorçage de la soufflerie.
Bakulu, Natungadio Florian. "Analyse et modélisation de la dynamique de jets décollés en tuyère supersonique". Thesis, Chasseneuil-du-Poitou, Ecole nationale supérieure de mécanique et d'aérotechnique, 2019. http://www.theses.fr/2019ESMA0020.
Pełny tekst źródłaThis thesis, conducted in collaboration with CNES and Pprime Institut, has the objective of enhancing the dynamic phenomena understanding present in supersonic rocket nozzle. These phenomena may cause lateral loads that can damage the nozzle.The study focused on an ideal nozzle geometry and 3 operating points. The work is based on the exploitation and analysis of experimental and numerical data. The experimental data come from a campaign carried out within the Pprime Institute involving measurements of wall pressure synchronized with measurements of velocity fields by PIV. In addition, a numerical part reproducing the experimental tests using high-performance numerical simulations based on hybrid RANS/LES approaches is carried out.The experimental and numerical data show a particular organization of the wall pressure fluctuations observed in some work whose origin remains unknown. The study shows that this organisation is also present in the velocity field of the jet where links with wall pressure have been established by correlation calculations. Numerical simulations show that such a coordination of the pressure field drives the lateral force dynamics. Some scenarios on the origin of this organised fluctuation are discarded by the use of reduced flow models
Zmijanovic, Vladeta. "Vectorisation fluidique de la poussée d'une tuyère axisymétrique supersonique par injection secondaire". Phd thesis, Université d'Orléans, 2013. http://tel.archives-ouvertes.fr/tel-00872072.
Pełny tekst źródłaBoccaletto, Luca. "Maîtrise du décollement de tuyère. Analyse du comportement d'une tuyère de type TOC et définition d'un nouveau concept : le BOCCAJET". Thesis, Aix-Marseille 1, 2011. http://www.theses.fr/2011AIX10012/document.
Pełny tekst źródłaThis research is in two parts. The objective of the first part is to analyse by experimental and numerical means the phenomenology of nozzle flow separation in transient and steady state conditions. The second part of this research work focuses on the reinterpretation of existing concepts of converging-diverging nozzles, leading to the proposal of a new supersonic expansion device, with improved flow separation characteristics.Experimental data, collected during the test campaign conducted at ONERA, have been analysed and are presented in the first part of this thesis. Obtained results highlight some peculiarities of the transient behavior of the nozzle, mostly dependent on the synchronisation between the start-up phase of the main jet and the grow-up of the wall film. These same experiments have been also used to investigate the unsteadiness of the flow separation, when nozzle feeding conditions are maintained constant. Appearance of characteristic frequencies has been highlighted and their origin has been investigated by CFD simulations.In the second part, a critical review of existing nozzle concepts was conducted. This allowed identifying a major gap in the definition of traditional supersonic nozzles, namely the absence of a "barrier" that can prevent the occurrence of the flow separation. Thus, in the second part of this thesis we propose a new nozzle concept. It is based on the combination of a small aerospike and a conventional nozzle (main flow). Such an arrangement allows solving the flow separation problem in nuce. The effectiveness of this concept has been proved by calculation and by an experimental test campaign
Mouronval, Anne-Sophie. "Etude numérique des phénomènes aéroélastiques en aérodynamique supersonique. Application aux tuyères propulsives". Phd thesis, INSA de Rouen, 2004. http://tel.archives-ouvertes.fr/tel-00011632.
Pełny tekst źródłaShams, Afaque. "Contribution à la simulation numérique des décollements d'écoulements turbulents induits par choc : application à l'écoulement sur-détendu de tuyère supersonique". Chasseneuil-du-Poitou, Ecole nationale supérieure de mécanique et d'aéronautique, 2010. http://www.theses.fr/2010ESMA0010.
Pełny tekst źródłaShock-induced flow separation and its subsequent reattachment are encountered in many configurations, such as supersonic inlets, transonic airfoils or rocket nozzles. These phenomena involve complex interactions of boundary layers with compression or expansion waves and exhibit a low-frequency unsteady behaviour which still requires a clear explanation. This study aims at better identifying the physical mechanisms which drive the global structure of these flows and suggesting improved numerical tools in order to predict these more accurately. The appearance of free and restricted separations in supersonic separated jets occuring in thrust optimized contour nozzles operating in over-expanded conditions is more particularly investigated while various hypothesis are tested to explain the evolution of the associated unsteady asymmetric wall pressure field in function of the nozzle pressure ratio. The numerical strategy proposed relies on a realizable extension of the Detached Eddy Simulation, combined with high order shock capturing schemes and an implicit time integration algorithm. This methodology is applied for a wide range of both constant or transient inflow conditions and leads to identify more accurately the appearance of free and restricted separations and the time-varying morphology of the flow during the transition process. For both flow regimes, the simulations are carried out for long-enough time to perform reliable statistical analysis and azimuthal expansion of the wall pressure field and thus investigate extensively the possible origins of the side-load activities
Deng, Jing. "Etude numérique des transferts conjugués paroi-fluide d'un écoulement e fluide compressible dans une tuyère". Phd thesis, Université de Technologie de Belfort-Montbeliard, 2011. http://tel.archives-ouvertes.fr/tel-00720654.
Pełny tekst źródłaBekka, Nadir. "Problématique des phénomènes des ondes de choc dans les tuyères supersoniques et leur interaction avec la structure". Electronic Thesis or Diss., Evry-Val d'Essonne, 2014. http://www.theses.fr/2014EVRY0005.
Pełny tekst źródłaThe problem of side loads occurring in rocket engine nozzles remains a major issue for the aerospace industry. Furthermore, the desire to reduce the overall mass of the launcher leads to the design of nozzles with increasing fineness, which, in turn, can pose aeroelastic problems. Indeed, it is well established that during the start-up and shutdown phases of a rocket engine, the structure interacts with the main flow, leading to the generation of aeroelastic effects. This interaction can further amplify the lateral loads and even put the integrity of the launcher at risk. Such phenomena can be addressed through a multiphysical approach, such as coupled numerical simulations. However, for complex problems such as coupled computation for 3D nozzles in turbulent flow, even with significant computational resources deployed, the time required to complete this type of numerical simulation remains exorbitant. Another alternative is to model these effects using relatively simple aeroelastic stability models, which allow for the detection of potential instabilities at a lower cost. Aeroelastic phenomena in nozzles operating under an overexpansion regime are thoroughly analyzed using aeroelastic stability models. Derived from the simplified Pekkari model, new aeroelastic stability models taking into account the viscous effects of the flow have been proposed. The coupling between the flow and the structure is achieved via the theory of small perturbations or piston theory. This is made possible by introducing a more realistic pressure profile through the use of Chapman's free interaction theory for uniform incident flow. The resulting formulation, of which the initial Pekkari model can be considered a special case, is based on the calculation of interaction length and relies on Michel's integral method for boundary layers, whether laminar or turbulent. Numerical calculations were performed using a weak coupling between a CFD code and a structural code, employing the transpiration method. This method, even limited to small displacements of the structure (linear case), generally allows for the prediction of instabilities. Data exchange between the two codes, fluid, and structure, was facilitated through a simple interface written in Fortran, allowing for dynamic data exchange. The results from the different models are presented in a comparative