Ce travail de thèse part d’un constat : d’importantes pertes thermiques sont observées lors de l’élaboration des matériaux du génie civil. Motivés par l’ajout d’une double enveloppe, les travaux contenus dans ce manuscrit visent à caractériser un échangeur de chaleur appliqué en paroi des fours rotatifs. Tout d’abord, un modèle intégré est développé, puis validé sur une centrale d’enrobage dont la paroi intérieure du four est munie de releveurs nécessaires au mélange des matériaux. Leur distribution dans la section transversale est estimée à partir d’une loi de déchargement granulaire. Les expérimentations numériques montrent que les transferts Gaz / Solide et Solide / Paroi dominent, ce dernier phénomène limitant les performances globales du procédé. L’ajout de l’échangeur sur paroi mobile est quant à lui exploré sur un banc d’essai instrumenté de type rotor-stator, avec entrée tangentielle. Développant un écoulement de type Taylor-Couette-Poiseuille, les transferts thermiques pariétaux sont caractérisés expérimentalement. Les résultats sont sans équivoque dans la gamme de nombres de Reynolds imposés : la contribution du mouvement axial surpasse le mouvement rotationnel turbulent. Une corrélation adimensionnelle basée sur le nombre de Nusselt est proposée afin d’estimer numériquement l’effet de l’échangeur sur les profils de température internes dans le four. Enfin, les structures tourbillonnaires de l’écoulement dans l’espace annulaire sont étudiées à partir d’un code de mécanique des fluides numériques utilisant la Simulation aux Grandes Echelles. Les simulations permettent de décrire les cellules contrarotatives au sein de la couche limite turbulente dont l’amplitude et la fréquence de passages sont reliées aux paramètres de fonctionnement de l’échangeur (débit axial et vitesse de rotation du four). / This work results on a finding: the heat loss from rotary kiln represents a significant energy amount during materials processing in civil engineering domain. Motivated by traditional energy recovery methods from heat exchanger, this thesis is aimed at providing their rigorous thermodynamic diagnostics. Firstly, a thermal-granular model is developed, and then validated in asphalt plant whose the rotary kiln is composed of flights to ensure the materials mixing. Their cross-section distribution is calculated from a granular discharge law. The numerical experiments showed an increase of heat transfer phenomena between gases and solids, and those between the solids and the wall, this latter phenomenon limiting the process performances. Heat recovery exchanger applied to the rotary kiln is studied from a semi-industrial pilot based on a rotor stator configuration including a tangential inlet. Developing a Taylor-Couette-Poiseuille flow, the heat transfer results are undoubted in the range of the studied Reynolds numbers: the axial motion contribution is larger than the rotational turbulent motion. A dimension less criterion is proposed in order to be applied to the aforementioned integrated model including the heat exchanger applied to the rotary kiln, its effect being assessed upon the internal thermalprofiles. Finally, the vortices flow structure within the annular gap exchanger is studied from Large Eddy simulation. The amplitude and frequency passage of the contrarotatives cells located in the turbulent boundary layer are connected to the process parameters (the axial flowrate and the kiln shell rotation).

Les calculs d'écoulements stationnaires peuvent être considérés comme efficace si l?état stationnaire est atteint pour un temps CPU réduit mais aussi si la place mémoire utilisée reste faible; cette dernière exigence devient primordiale pour les applications industrielles où le nombre de points de calcul est très important. Ceci vaut également pour les écoulements instationnaires, désormais classiquement résolus via une approche pas-de-temps dual pour laquelle les états physiques successifs sont vus comme des états stationnaires vis-à-vis d'un temps fictif. Le besoin crucial de méthodes implicites à faible encombrement mémoire a conduit au développement de traitements sans matrice. Pour les applications qui intéressent le CEA, à savoir la simulation d'écoulements réactifs multi-espèces à l'intérieur d'une enceinte de réacteur nucléaire à eau pressurisée, les méthodes doivent être assez versatiles pour traiter la gamme d'écoulements allant du quasi-incompressible au fortement compressible. Le préconditionnement bas-Mach des équations de Navier-Stokes permet d'appliquer en régime incompressible les schémas initialement conçus pour la simulation des écoulements compressibles. Le présent travail montre comment obtenir un traitement implicite sans matrice pour tout régime d'écoulement lorsque la phase implicite contient une matrice de préconditionnement; l'efficacité intrinsèque du schéma implicite sans matrice couplé à une technique de relaxation de type Jacobi par point (PJ) ou Symmetric Gauss-Seidel (SGS) est étudiée grâce à une analyse de Von Neumann; puis des comparaisons avec des méthodes implicites blocs standards sont effectuées. La méthode implicite sans matrice est finalement implémentée au sein du code non-structuré CAST3M et elle est appliquée à la modélisation d'un Té de mélange à faible nombre de Mach. Le schéma implicite sans matrice constitue une alternative compétitive pour la simulation des écoulements compressibles et faiblement compressibles en maillages non-structurés.

This work deals with spatially-evolving supersonic turbulent boundary layers over adiabatic and cold walls at M∞ = 2 and up to Re0 ≈ 2600 using 3 different SGS models. The numerical methodology is based on high-order split-centered scheme to discretize the convective fluxes of the Navier-Stokes equations . For the adiabatic case, it is demonstrated that all SGS models require a comparable minimum grid-refinement in order to capture accurately the near-wall-turbulence. Overall, the models exhibit correct behavior when predictiong the dynamic properties, but show different performances for the temperature distribution in the near-wall region. For the isothermal case, it is found that the compressibility effects are not enhanced due to the wall cooling. As expected, the total temperature fluctuations are not negligible in the near-wall region. The study shows that the anti-correlation linking both velocity and temperature fields, derived from the Morkovin's hypothesis, is not satisfied.

Cette thèse entre dans le cadre du projet Hélimaintenance ; un project labellisé par le pôle de compétitivité Français Aérospace-Valley, qui vise à construire un centre dédié à la maintenance des hélicoptères civils qui soit capable de lancer des travaux en R&D dans le domaine. Notre travail consiste à prendre en considération les incertitudes dans la planification et l'ordonnancement de projets et résoudre les problèmes Rough Cut Capacity Planning, Resource Leveling Problem et Resource Constraint Project Scheduling Problem sous incertitudes. L'incertitude est modélisée avec l'approche floue/possibiliste au lieu de l'approche stochastique ce qui est plus adéquat avec notre cas d'étude. Trois types de problèmes ont été définis dans cette étude à savoir le Fuzzy Rough Cut Capacity Problem (FRCCP), le Fuzzy Resource Leveling Problem (FRLP) et le Fuzzy Resource Constraint Project Scheduling Problem (RCPSP). Un Algorithme Génétique et un Algorithme "Parallel SGS" sont proposés pour résoudre respectivement le FRLP et le FRCPSP et un Recuit Simulé est proposé pour résoudre le problème FRCCP.

Least Square Kinetic Upwind Method (LSKUM) belongs to the class of mesh-less method that solves compressible Euler equations of gas dynamics. LSKUM is kinetic theory based upwind scheme that operates on any cloud of points. Euler equations are derived from Boltzmann equation (of kinetic theory of gases) after taking suitable moments. The basic update scheme is formulated at Boltzmann level and mapped to Euler level by suitable moments. Mesh-less solvers need only cloud of points to solve the governing equations. For a complex configuration, with such a solver, one can generate a separate cloud of points around each component, which adequately resolves the geometric features, and then combine all the individual clouds to get one set of points on which the solver directly operates. An obvious advantage of this approach is that any incremental changes in geometry will require only regeneration of the small cloud of points where changes have occurred. Additionally blanking and de-blanking strategy along with overlay point cloud can be adapted in some applications like store separation to avoid regeneration of points. Naturally, the mesh-less solvers have advantage in tackling complex geometries and moving components over solvers that need grids. Conventionally, higher order accuracy for space derivative term is achieved by two step defect correction formula which is computationally expensive. The present solver uses low dissipation single step modified CIR (MCIR) scheme which is similar to first order LSKUM formulation and provides spatial accuracy closer to second order. The maximum time step taken to march solution in time is limited by stability criteria in case of explicit time integration procedure. Because of this, explicit scheme takes a large number of iterations to achieve convergence. The popular explicit time integration schemes like four stages Runge-Kutta (RK4) are slow in convergence due to this reason. The above problem can be overcome by using the implicit time integration procedure. The implicit schemes are unconditionally stable i.e. very large time steps can be used to accelerate the convergence. Also it offers superior robustness. The implicit Lower-Upper Symmetric Gauss-Seidel (LU-SGS) scheme is very attractive due to its low numerical complexity, moderate memory requirement and unconditional stability for linear wave equation. Also this scheme is more efficient than explicit counterparts and can be implemented easily on parallel computers. It is based on the factorization of the implicit operator into three parts namely lower triangular matrix, upper triangular matrix and diagonal terms. The use of LU-SGS results in a matrix free implicit framework which is very economical as against other expensive procedures which necessarily involve matrix inversion. With implementation of the implicit LU-SGS scheme larger time steps can be used which in turn will reduce the computational time substantially. LU-SGS has been used widely for many Finite Volume Method based solvers. The split flux Jacobian formulation as proposed by Jameson is most widely used to make implicit procedure diagonally dominant. But this procedure when applied to mesh-less solvers leads to block diagonal matrix which again requires expensive inversion. In the present work LU-SGS procedure is adopted for mesh-less approach to retain diagonal dominancy and implemented in 2-D and 3-D solvers in matrix free framework. In order to assess the efficacy of the implicit procedure, both explicit and implicit 2-D solvers are tested on NACA 0012 airfoil for various flow conditions in subsonic and transonic regime. To study the performance of the solvers on different point distributions two types of the cloud of points, one unstructured distribution (4074 points) and another structured distribution (9600 points) have been used. The computed 2-D results are validated against NASA experimental data and AGARD test case. The density residual and lift coefficient convergence history is presented in detail. The maximum speed up obtained by use of implicit procedure as compared to explicit one is close to 6 and 14 for unstructured and structured point distributions respectively. The transonic flow over ONERA M6 wing is a classic test case for CFD validation because of simple geometry and complex flow. It has sweep angle of 30° and 15.6° at leading edge and trailing edge respectively. The taper ratio and aspect ratio of the wing are 0.562 and 3.8 respectively. At M∞=0.84 and α=3.06° lambda shock appear on the upper surface of the wing. 3¬D explicit and implicit solvers are tested on ONERA M6 wing. The computed pressure coefficients are compared with experiments at section of 20%, 44%, 65%, 80%, 90% and 95% of span length. The computed results are found to match very well with experiments. The speed up obtained from implicit procedure is over 7 for ONERA M6 wing. The determination of the aerodynamic characteristics of a wing with the control surface deflection is one of the most important and challenging task in aircraft design and development. Many military aircraft use some form of the delta wing. To demonstrate the effectiveness of 3-D solver in handling control surfaces and small gaps, implicit 3-D code is used to compute flow past clipped delta wing with aileron deflection of 6° at M∞ = 0.9 and α = 1° and 3°. The leading edge backward sweep is 50.4°. The aileron is hinged from 56.5% semi-span to 82.9% of semi-span and at 80% of the local chord from leading edge. The computed results are validated with NASA experiments

Cette thèse traite des transferts pariétaux dans les écoulements turbulents supersoniques via la simulation des grandes échelles turbulentes. Des couches limites adiabatique et refroidie évoluant à Mach M∞ = 2 et à Reynolds Re0 ≈ 2600 sont considérées. Les simulations numériques utilisent un schéma split-centered d’ordre élevé pour la discrétisation des flux convectifs. Les résultats obtenus sont comparés aux simulations numériques directes (DNS) disponibles dans la littérature. Plusieurs modèles de sous-maille ont été testés et validés. Il a été montré que ces modèles exigent un minimum de raffinement de maillage afin de capturer les structures les plus énergétiques présentes en proche paroi. Les modèles montrent des performances différentes pour la distribution de la température à la paroi. Pour le cas d’une paroi refroidie, les fluctuations de température totale ne sont pas négligeables dans la région proche-paroi. Et l’anticorrélation (u’, T’) se basant sur l’hypothèse de Morkovin n’est pas satisfaite. / This work deals with spatially-evolving supersonic turbulent boundary layers over adiabatic and cold walls at M∞ = 2 and up to Re0 ≈ 2600 using 3 different SGS models. The numerical methodology is based on high-order split-centered scheme to discretize the convective fluxes of the Navier-Stokes equations . For the adiabatic case, it is demonstrated that all SGS models require a comparable minimum grid-refinement in order to capture accurately the near-wall-turbulence. Overall, the models exhibit correct behavior when predictiong the dynamic properties, but show different performances for the temperature distribution in the near-wall region. For the isothermal case, it is found that the compressibility effects are not enhanced due to the wall cooling. As expected, the total temperature fluctuations are not negligible in the near-wall region. The study shows that the anti-correlation linking both velocity and temperature fields, derived from the Morkovin's hypothesis, is not satisfied.