A methodology is formulated for the solution of the inverse problem concerned with the reconstruction of multi-dimensional heat fluxes for film cooling applications. The motivation for this study is the characterization of complex thermal conditions in industrial applications such as those encountered in film cooled turbomachinery components. The heat conduction problem in the metal endwall/shroud is solved using the boundary element method (bem), and the inverse problem is solved using a genetic algorithm (ga). Thermal conditions are overspecified at exposed surfaces amenable to measurement, while the temperature and surface heat flux distributions are unknown at the film cooling hole/slot walls. The latter are determined in an iterative process by developing two approaches. The first approach, developed for 2d applications, solves an inverse problem whose objective is to adjust the film cooling hole/slot wall temperatures and heat fluxes until the temperature and heat flux at the measurement surfaces are matched in an overall heat conduction solution. The second approach, developed for 2d and 3d applications, is to distribute a set of singularities (sinks) at the vicinity of the cooling slots/holes surface inside a fictitious extension of the physical domain or along cooling hole centerline with a given initial strength distribution. The inverse problem iteratively alters the strength distribution of the singularities (sinks) until the measuring surfaces heat fluxes are matched. The heat flux distributions are determined in a post-processing stage after the inverse problem is solved. The second approach provides a tremendous advantage in solving the inverse problem, particularly in 3d applications, and it is recommended as the method of choice for this class of problems. It can be noted that the ga reconstructed heat flux distributions are robust, yielding accurate results to both exact and error-laden inputs. In all cases in this study, results from experiments are simulated using a full conjugate heat transfer (cht) finite volume models which incorporate the interactions of the external convection in the hot turbulent gas, internal convection within the cooling plena, and the heat conduction in the metal endwall/shroud region. Extensive numerical investigations are undertaken to demonstrate the significant importance of conjugate heat transfer in film cooling applications and to identify the implications of various turbulence models in the prediction of accurate and more realistic surface temperatures and heat fluxes in the cht simulations. These, in turn, are used to provide numerical inputs to the inverse problem. Single and multiple cooling slots, cylindrical cooling holes, and fan-shaped cooling holes are considered in this study. The turbulence closure is modeled using several two-equation approach, the four-equation turbulence model, as well as five and seven moment reynolds stress models. The predicted results, by the different turbulence models, for the cases of adiabatic and conjugate models, are compared to experimental data reported in the open literature. Results show the significant effects of conjugate heat transfer on the temperature field in the film cooling hole region, and the additional heating up of the cooling jet itself. Moreover, results from the detailed numerical studies presented in this study validate the inverse problem approaches and reveal good agreement between the bem/ga reconstructed heat fluxes and the cht simulated heat fluxes along the inaccessible cooling slot/hole walls

Les motoristes aéronautiques souhaitent disposer de la représentation la plus fidèle possible du fonctionnement des propulseurs, dans une perspective d'amélioration continue de leurs performances. Les modèles numériques doivent donc intégrer au maximum les détails géométriques susceptibles d'influencer la physique de l'écoulement analysé. La prise en compte de tels effets technologiques s'avère difficile dans le contexte des solveurs structurés disponibles.Une stratégie hybride de prise en compte des effets technologiques fait coexister au sein d'un même domaine de calcul des zones structurées et non structurées. La flexibilité de génération d'un maillage non structuré permet une prise en compte aisée des détails géométriquement complexes tandis que la préservation de zones structurées dans une majeure partie du domaine de calcul permet de bénéficier de l'efficacité d'un solveur structuré. La présente thèse contribue au développement de cette stratégie hybride au sein du solveur elsA de l'ONERA en proposant des gains de précision et de robustesse par rapport à la version initialement développée pour établir la faisabilité et l'intérêt de l'approche. Après un état de l'art des techniques de discrétisation spatiale disponibles dans cette version initiale, différentes améliorations (techniques de moindres carrés, approche dite quasi-Green, méthode d'estimation des gradients aux faces) ont été analysées puis implémentées et validées sur des cas académiques. Le choix d'une stratégie hybride avec raccords coïncidents entre zones structurées et non-structurées conduit à des déformations de maillage dans la zone d'interface structuré / non-structuré qui ont exigé le développement supplémentaire de techniques d'amélioration de la robustesse (limiteurs physiques ou géométriques). Le solveur hybride rassemblant ces différentes fonctionnalités a permisde simuler avec succès des géométries d'aubes isolées dotées d'effets technologiques tels que congé de raccordement, trous de refroidissement, fentes de bord de fuite, cheminées internes d'alimentation. Enfin, une stratégie permettant l'utilisation de l'approche hybride en étage complet a été proposée et appliquée à la simulation hybride de l'interaction rotor/stator pour la configuration VKI-BRITE CT3, en stationnaire et en instationnaire, respectivement via une condition de plan de mélange et une condition de chorochronicité. / The aerospace engine manufacturers wish to rely on the most accurate description of their propulsion systems in order to continuously improve their performance levels. Therefore, numerical models must include as much as possible geometrical details likely to impact the physics of the flow under study. Taking into account such technological effects turns out to be a difficult task when working with available structured solvers. A hybrid strategy takes advantage of structured and unstructured zones within the same computational domain in order to efficiently describe technological effects. Geometrically complex local details are easily accounted for thanks to the flexibility of unstructured grid generation while keeping structured zones in the remainder of the flow domain allows to benefit from the tried and tested structured solver efficiency. The present work contributes to the development of such a hybrid strategy in ONERA elsA solver and enhances accuracy and robustness with respect to the solver initially developed to establish the feasibility and interest of hybridization. Following a review of the space discretization techniques available in the initial solver, several improvements (least square techniques, quasi-Green approach, computation of face gradients) have been analysed, then implemented and validated for academic test-cases. The choice of a hybrid strategy with coincident matching between structured and unstructured zones leads to highly deformed cells in the structured / unstructured interface region, requiring the development of supplementary robustness improvement techniques (physics- or geometry-based limiters). The hybrid solver gathering these various options allows to successfully compute isolated blade geometries including technological effects such as blade fillet, cooling holes, trailing edge cutbacks, internal coolant supply channel. Finally, a structured / unstructured strategy has been proposed and applied to the hybrid simulation of a rotor/stator interaction for the steady and unsteady