O principal objetivo desta tese é estudar os efeitos inerciais e de pressão do escoamento médio sobre o próprio escoamento médio de jatos bi-dimensionais confinados. Os escoamentos considerados no presente trabalho são turbulentos, isotérmicos, incompressíveis e compostos por fluidos simples. A introdução e a revisão bibliográfica são feitas por meio da apresentação: das motivações tecnológicas e fundamentais para a escolha do tema da presente tese; do cenário no qual a abordagem adotada está inserida; dos parâmetros adimensionais usualmente adotados na literatura para caracterizar os jatos bidimensionais confinados (parâmetros clássicos); e dos dados experimentais levantados na literatura na forma de correlações semi-empíricas, e de perfis de propriedades do escoamento. A presente tese desenvolve uma abordagem integral e adimensional para jatos confinados. As hipóteses adotadas nesta abordagem são aquelas relativas a escoamentos em camada fina cisalhante, e a escoamentos não dissipativos. A abordagem é baseada em balanços integrais de massa e quantidade de movimento. Os termos de quantidade de movimento são classificados como inerciais ou de pressão; e como fluxos, forças ou fontes. Esta classificação permite analisar os efeitos considerados pelos parâmetros adimensionais clássicos. Os parâmetros clássicos não satizfazem simultaneamente às seguintes condições: ser baseado em uma superfície de controle fechada; e ter os efeitos inerciais e de pressão separados em parâmetros distintos. Desta forma, são desenvolvidos dois parâmetros adimensionais novos. Estes parâmetros novos são usados na definição de variáveis adimensionais cuja finalidade é obter uma regra de escalonamento apropriada. A regra de escalonamento desenvolvida é validada por meio de sua aplicação a três bancos de dados de literatura. Esta aplicação mostra a influência dos efeitos inerciais e de pressão sobre o escoamento. A qualidade dos dados experimentais de literatura e próprios também é avaliada pela aplicação desta mesma regra de escalonamento. O túnel de vento construído para estudo de jatos confinados axi-simétricos é apresentado por meio: dos requisitos de projeto; dos critérios de projeto; e da descrição dos componentes. Este túnel possui seção de teste com 300mm de diâmetro e 1500mm de comprimento; contração com razão de área de 4 : 1 e lanças de ar com diâmetros de 10mm, 40mm, 75mm e 150mm. Os procedimentos experimentais adotados na caracterização do escoamento do túnel de vento axi-simétrico incluem: a técnica de determinação do tensor das tensões de Reynolds e do vetor velocidade média em função de medições de velocidade média e de tensão normal de Reynolds em 6 direções distintas; a validação desta técnica; e as correções de posicionamento e de direcionamento do intrumento de medição. O instrumento de medição utilizado foi um anemômetro a laser (LDV). As principais contribuições da presente tese são as seguintes: redesenvolvimento dos parâmetros adimensionais clássicos de jatos confinados por meio de uma metodologia e nomenclatura unificada; proposição de dois parâmetros adimensionais para jatos confinados, um para efeitos inerciais e outro para efeitos de pressão; incremento do banco de dados experimentais referentes a jatos confinados; construção de um túnel de vento axi-simétrico para estudo de jatos confinados; e descoberta da existência de similaridade em jatos confinados com gradiente de pressão elevado. / The main objective of this thesis is to study the mean flow inertial and pressure effects on the mean flow itself in two-dimensional confined jets. The flows considered in the present work are turbulent, isothermal, incompressible and single-fluid. The introduction and the bibliographical review are done by the following presentations: technological and fundamental motivations for the choice of the thesis subject; the scene where the adopted approach is included; dimensionless parameters usually adopted in the literature for two-dimensional confined jets characterization (classic parameters); and experimental data found in literature as semi-empirical correlation, and as mean flow properties profiles. This thesis develops an integral and dimensionless approach for confined jets. The hypotheses adopted in such approach are the thin shear layer approximation, and the non-dissipative flow assumption. The approach is based on mass and momentum integral balances. The terms are classified as inertial or as pressure; and as flux, as force, or as source. Such classification allows the analysis of the effects considered by the dimensionless classic parameters. The classic parameters do not satisfy the following conditions simultaneously: to be based on a closed control surface; and to separate the inertial and pressure effects in distinct parameters. Due to this, two new dimensionless parameters are developed. The new dimensionless parameters are used in dimensionless variables definition whose purpose is to obtain a proper scaling rule. The developed scaling rule is validated applying it to three data banks from literature. This application shows the inertial and pressure effects on the flow. The quality of the literature and the own data bank is evaluated by this scaling rule application. The wind tunnel built for axi-symmetric confined jets studies is presented by: project requirements; project criteria; and components description. This tunnel has a test section with 300mm in diameter and 1500mm in length; contraction area rate of 4 : 1; and air guns with 10mm, 40mm, 75mm and 150mm in diameters. The procedures adopted in the axi-symmetric wind tunnel flow characterization include: the scheme to determine the Reynolds stress tensor and the mean velocity vector from mean velocity and normal Reynolds stress measurements in six distinct directions; this scheme validation; and the positioning and directioning probe corrections. The instrument used was a laser Doppler velocimeter. The main contributions of the present thesis are the following: redevelopment of the confined jets classic dimensionless parameters through an unified methodology and nomenclature; the proposition of two new confined jets dimensionless parameters, one for inertial effects and other for pressure effects. improvement of experimental data bank regarding confined jets; construction of an axi-symmetric wind tunnel for confined jet studies; and the discovery of the similarity existence in confined jets with high pressure gradient.

The present study deals with the effects of sparsely distributed three-dimensional elements on two-dimensional (2-D) and three-dimensional (3-D) turbulent boundary layers (TBL) such as those that occur on submarines, ship hulls, etc. This study was achieved in three parts: Part 1 dealt with the cylinders when placed individually in the turbulent boundary layers, thereby considering the effect of a single perturbation on the TBL; Part 2 considered the effects when the same individual elements were placed in a sparse and regular distribution, thus studying the response of the flow to a sequence of perturbations; and in Part 3, the distributions were subjected to 3-D turbulent boundary layers, thus examining the effects of streamwise and spanwise pressure gradients on the same perturbed flows as considered in Part 2. The 3-D turbulent boundary layers were generated by an idealized wing-body junction flow. Detailed 3-velocity-component Laser-Doppler Velocimetry (LDV) and other measurements were carried out to understand and describe the rough-wall flow structure. The measurements include mean velocities, turbulence quantities (Reynolds stresses and triple products), skin friction, surface pressure and oil flow visualizations in 2-D and 3-D rough-wall flows for Reynolds numbers, based on momentum thickness, greater than 7000. Very uniform circular cylindrical roughness elements of 0.38mm, 0.76mm and 1.52mm height (k) were used in square and diagonal patterns, yielding six different roughness geometries of rough-wall surface. For the 2-D rough-wall flows, the roughness Reynolds numbers, based on the element height (k) and the friction velocity, range from 26 to 131. Results for the 2-D rough-wall flows reveal that the velocity-defect law is similar for both smooth and rough surfaces, and the semi-logarithmic velocity-distribution curve is shifted by an amount depending on the height of the roughness element, showing that this amount is a function of roughness Reynolds number and the wall geometry. For the 3-D flows, the data show that the surface pressure gradient is not strongly influenced by the roughness elements. In general, for both 2-D and 3-D rough-wall TBL, the differences between the two roughness patterns (straight and diagonal), as regards the mean velocities and the Reynolds stresses, are limited to about 3 roughness element heights from the wall. The study on single elements revealed that the separated shear layers emanating from the top of the elements form a pair of counter rotating vortices that dominate the downstream flow structure. These vortices, termed as the roughness top vortex structure (RTVS), in conjunction with mean flow, forced over and around the elements, are responsible for the production of large Reynolds stresses in the neighborhood of the element height aft of the elements. When these elements are placed in a distribution, the effects of RTVS are not apparent. The roughness elements create a large region of back flow behind them which is continuously replenished by faster moving fluid flowing through the gaps in the rough-wall. The fluid in the back flow region moves upward as low speed ejections where it collides with the inrushing high speed flow, thus, leading to a strong mixing of shear layers. This is responsible for the generation of large levels of turbulent kinetic energy (TKE) in the vicinity of the element height which is transported, primarily, by turbulent diffusion. As regards the 3-D rough-wall TBL, the effect of flow three-dimensionality is seen in the large skewing of the distributions of mean velocities, Reynolds stresses and TKE, aft of the elements. In general, the regions of large TKE production-rates seem to propagate in the direction of the local velocity vector at the element height. The data-sets also enable the extraction of the turbulent flow structure to better describe the flow physics of these rough-wall turbulent boundary layers. / Ph. D.

This thesis presents some results from an experimental study of three-dimensional turbulent tip gap flows in the linear cascade wind tunnel, for two different tip gap clearances (t/c=1.65% and 3.3%). The experiments focus on near-wall flow field measurements for the stationary wall and moving wall, and static pressure measurement on the low end-wall for the stationary wall case. The representative flows were pressure driven, three-dimensional turbulent boundary layers in the linear cascade tunnel for the stationary wall case, and the combination of the pressure driven and shear driven flow for the moving wall case. Several experimental techniques are used in the studies: a three-orthogonal-velocity-component fiber-optic laser Doppler anemometer (3D-LDA) system, surface oil flow visualization, and a scanivalve system for static pressure measurement through pressure ports on the end-wall. From the details of the oil flow visualization pattern on the end-wall, some features of the passage flow, cross flow, and the tip leakage vortex in this cascade flow were captured. Oil flow visualization on the blade surface reveals the reattachment of the tip leakage vortex on the blade surface. The static pressure results on the lower end-wall and mid-span of the blade show huge pressure drop on the lower end-wall from the pressure side to the suction side of the blade and from mid-span to the lower end wall. The end-wall skin friction velocity is calculated from near-wall LDA data and pressure gradient data using the near-wall momentum equation. The statistics of Reynolds stresses and triple products in two-dimensional turbulent boundary layer and three-dimensional turbulent boundary layer was examined using a velocity fluctuation octant analysis in three different coordinates (the wall collateral coordinates, the mid tip gap coordinates, and the local mean flow angle coordinates). The velocity fluctuation octant analysis for the two-dimensional turbulent boundary layer reveals that ejections of the low speed streaks outward from the wall and the sweeps of high speed streaks inward toward the wall are the dominant coherent motions. The octant analysis for the three-dimensional turbulent boundary layer in the tip gap shows that the dominant octant events are partially different from those in the two-dimensional turbulent boundary layer, but ejection and sweep motions are still the dominant coherent motions. For the three-dimensional turbulent boundary layer in the moving wall flow, the near-wall shear flow reinforces the sweep motion to the moving wall and weakens the out-ward ejection motion in the shear flow dominant region. Between the passage flow and the shear flow, is the interaction region of the high speed streaks and the low speed streaks. This is the first time that the coherent structure of the three-dimensional turbulent boundary in the linear cascade tip gap has been studied. / Master of Science

With the goal to continue interplanetary exploration and search for past or existent life on Mars, software and hardware for unmanned subsurface drills are being developed. Unlike drilling on Earth, interplanetary exploration drills operate with very low available power and require on-board integrated health monitoring systems, with quick-response recovery procedures, under complete autonomous operations. As many drilling faults are not known a priori, Earth-based direction and control of an unmanned interplanetary drilling operation is not practical. Such missions also require advanced robotic systems that are more susceptible to structural and mechanical failures, which motivates a need for structural health monitoring techniques relevant to interplanetary exploration systems. Structural health monitoring (SHM) is a process of detecting damage or other types of defects in structural and mechanical systems that have the potential to adversely affect the current or future performance of these systems. Strict requirements for interplanetary drilling missions create unique research problems and challenges compared with SHM procedures and techniques developed to date. These challenges include implementing sensors and devices that do not interfere with the drilling operation, producing "real-time" diagnostics of the drilling condition, and developing an automation procedure for complete autonomous operations. Thus, the completed thesis work presents basic research leading to the dynamic analysis of rotating structures with specific application to interplanetary subsurface drill systems, and the formulation of an autonomous, real-time, dynamics-based SHM technique for drilling applications. This includes modeling and validating the structural dynamic system, with and without damage or faults, for a prototype interplanetary subsurface drill, exploring the use of Laser Doppler Velocimeter sensors for use in real-time SHM, developing signal filters to remove inherent harmonic components from the dynamic signal of rotating structures, developing an automation procedure with the associated software, and validating the SHM system through laboratory experiments and field tests. The automated dynamics-based structural health monitoring technique developed in this thesis presents advanced research accomplishments leading to real-time, autonomous SHM, and it has been validated on an operating dynamic system in laboratory and field tests. The formulated SHM and drilling operation also met or exceeded all specified requirements. Other major contributions of this thesis work include the formulation and demonstration of real-time, autonomous SHM in rotating structures using Laser Doppler Velocimeter sensors.

La réduction de la consommation des bâtiments passe par : l'économie d'énergie, l'efficacité énergétique et l'utilisation des énergies renouvelables. Sur ce dernier point, l'intégration à grande échelle de composants photovoltaïques (PV) est une solution. Le rendement et la durée de vie des cellules PV en silicium cristalin diminuant avec l'augmentation de leur température de fonctionnement, il est essentiel de mettre au point des configurations d'intégration limitant leur échauffement. L'intégration en configuration de double-peau - la surface PV est séparée du bâtiment par une lame d'air - est une solution prometteuse. Sous l'effet de la chaleur, un écoulement de convection naturelle se met en place entre les deux parois, refroidissant ainsi les panneaux PV. Cet écoulement peut également servir de moteur pour la ventilation en été, et de préchauffage de l'air en hiver. Cette étude, expérimentale, fait partie d'un projet visant à comprendre le fonctionnement des double-peaux PV en analysant séparément les différents phénomènes physiques avant de prendre en compte l'ensemble des couplages. Elle porte plus particulièrement sur la convection naturelle au sein des double-façades verticales. Ici, la double-peau est modélisée par un canal vertical dont les deux parois principales sont chauffées sous des conditions de flux imposé. Un banc d'essais a été développé pour étudier la convection naturelle dans un canal vertical en eau. L'eau a été choisie pour se placer dans le cas d'un écoulement de convection pure (pas de rayonnement entre les parois). C'est un canal vertical de 65 cm de haut avec un écartement réglable placé dans une cuve de 1,5 m de haut contenant 160 L d'eau. Les parois sont chauffées à l'aide de 24 chaufferettes indépendantes délivrant un flux de chaleur uniforme, ce qui permet d'appliquer différentes configurations de chauffage. Des mesures de flux et de température sont réalisées au niveau des parois, et un système couplant de la velocimétrie laser Doppler deux composantes à un micro-thermocouple (25 μm) a été développé pour avoir accès aux vitesses verticale et horizontale et à la température dans le canal. Ce banc et son instrumentation sont décrits et les incertitudes de mesure associées ont été caractérisées. La configuration de chauffage uniforme symétrique a été étudiée ici pour différentes puissances injectées. Les profils de vitesse et de température moyennes mettent en évidence la présence d'un changement de régime d'écoulement dans le canal pour un nombre de Rayleigh indéntifié. L'étude approfondie des profils des fluctuations de vitesse et de température a permis de mettre au point une modélisation comportementale de ce changement de régime. De plus, une première approche est développée pour évaluer la pression dans le canal à partir de l'analyse et de l'estimation des différents termes de l'équation de conservation de la quantité de mouvement.

This thesis deals with design and implementation of extension module that enables 2D scanning with single-point interferometer. Afterwards is here solved question of software, which output data can be visualized in ModalVIEW by ABSignal company. My work also contains an overview of LDV sensors and scan systems, which are used to laser beam steering.

The goal of cancer chemotherapy is to develop effective, safe, and well-tolerated medications. The over-expression of certain receptors on cancer cell membrane provides a basis for active targeting by not only specific interaction between drug delivery system and cells, but also facilitated cellular uptake via receptor-mediated endocytosis. In this study, LDV oligomers up to six LDV repeating units were synthesized via solid phase peptide synthesis method, and evaluated as drug carrier as well as targeting moiety to deliver doxorubicin (Dox) to human malignant melanoma cells (A375), which over-express integrin α 4 β 1 . Cells expressing different levels of integrin α 4 β 1 or modulated using integrin α 4 -specific siRNA knock-down technique were verified by western blot and PCR. Magnetic beads with tripeptides LDV, VDL, or LNV on the surface were used in the binding specificity studies. Results verified that LDV was the minimally required ligand sequence for the specific binding to integrin α 4 β 1 , of which the interaction depends on the amount of integrin and can be utilized for the design of targeted drug delivery. The studies on A375 cells uptake of FITC-labeled LDV oligomers examined the effects of EDTA, temperature, endocytosis inhibitor, and competitive ligand. Cellular uptake mechanism was revealed to be temperature-dependent, receptor-mediated endocytosis, involving the specific interaction between LDV and integrin α 4 β 1 . The internalization extent of LDV monomer was the highest and was also inhibited to the most by the addition of free LDV when compared to other LDV oligomers. Cytotoxicity profiles of Dox-conjugated LDV oligomers were obtained on wild-type A375, integrin α4 knock-down A375, and normal human epithelial keratinocytes (NHEK) using SRB assay. A significant decrease (3∼6 folds) in the cytotoxicity of oligo(LDV)-Dox on A375 cells were observed when the integrin α4 expression was knocked down by ∼50%. Cytotoxicity further decreased on NHEK, which has the lowest integrin α4 expression among three cell lines. In contrast to oligo(LDV)-Dox, free Dox was not able to differentiate between cancerous and normal cells. This result demonstrated the potential of oligo(LDV) as targeting ligand. However, increase of repeating LDV unit did not lead to any apparent trend in cytotoxicity capacity. To facilitate the intracellular Dox release, hydrazone bond (HYD) was introduced between LDV and Dox. In vitro Dox release profiles in pH 6.0, 7.4, and rat plasma proved the pH-sensitivity of LDV-HYD-Dox. Cytotoxicity studies showed an increased cytotoxic effect of LDV-HYD-Dox when compared with LDV-Dox on wild-type A375 (2.5 times), knock-down A375 (1.5 times); while no significant difference in cytotoxicity on NHEK was observed. In vivo animal study supported the in vitro findings on LDV-HYD-Dox, which showed a significant inhibition of tumor growth and longest mice life span when compared to free Dox, poly(L,D,V)-Dox, and LDV-Dox, with averagely only ¼ of the tumor size and almost twice the life span of that from the free Dox group. In conclusion, based on the concept of specific interaction between LDV and integrin α 4 β 1 , oligo(LDV)-Dox targeted drug delivery system was developed and proved to be effective in the delivery of Dox to melanoma cells.

L’étude présentée dans cette thèse relève de la mécanique des fluides expérimentale et numérique appliquée aux écoulements pariétaux de refroidissement de chambres de combustion aéronautiques. En présence de phénomènes thermo-acoustiques, comme les instabilités de combustion, il est important d’évaluer si les capacités de l’écoulement pariétal à protéger les parois de chambre restent suffisantes. C’est ainsi que nous nous sommes intéressés aux écoulements de paroi multiperforée soumis à une excitation acoustique. Dans ce but, le banc d’essais MAVERIC a été amélioré grâce à l’installation d’un système qui permet de forcer acoustiquement l’écoulement transverse dans lequel les jets pariétaux débouchent. Nous avons pu alors mettre en évidence la forte sensibilité de ce type d’écoulements à l’excitation acoustique. Le bon accord entre les résultats expérimentaux et les simulations numériques aux grandes échelles (LES) effectuées est très encourageant dans le cas d’un forçage par onde stationnaire. Le forçage par onde progressive, étudié uniquement par simulations numériques, s’est révélé être capable de modifier significativement la topologie de l’écoulement. Enfin, à partir de l’outil numérique AVBP-AVTP qui permet le couplage de calculs fluide-solide, nous avons réalisé une étude de l’influence de la présence d’une excitation acoustique sur le comportement thermique de l’écoulement autour d’une paroi multiperforée de chambre de combustion. / This experimental and numerical study in the field of fluid mechanics deals with jets-in cross flow configurations that are relevant for the cooling of aero engine combustion chambers. Indeed, in presence of instabilities it is important to determine to which extent the film cooling is able to do its job of preserving the combustion chamber walls from the thermal load. The test facility MAVERIC has been upgraded in order to acoustically force the crossflow in which the jets are discharging. The strong sensitivity of the overall flow unsteady properties to the presence of the acoustic forcing has been clearly evidenced. The agreement between the experimental results and large-eddy simulations proved to be quite encouraging for a stationary acoustic wave whereas the case of a propagating acoustic wave investigated only numerically reveals also quite a significant change of the flow topology. In this context, the effect of the acoustic forcing on the wall thermal behavior has been analyzed thanks to the use of the fluid-solid coupled AVBP-AVTP solver.

Afin d’alléger les moteurs d’avions et diminuer la consommation de carburant, les industriels tendent à rendre plus compact le système de compression de leurs moteurs, qui représente environ 40% de la masse totale. Or, à taux de compression global égal, la réduction du nombre d’étages implique une charge aérodynamique plus élevée par étage. Cela augmente d’autant les risques de décollements sur les aubes et la dégradation des performances. L’aspiration de la couche limite sur les aubages s’est révélée très prometteuse pour supprimer ces décollements néfastes et satisfaire aux besoins de charge aérodynamique élevée. Cependant, l’aspiration modifie fortement la distribution de pression statique à la paroi des aubes, rendant les approches de conception traditionnelles inadaptées. L’objectif de ce travail de thèse est donc de proposer une nouvelle méthode et de nouveaux critères de conception d’aubages fortement chargés, intégrant l’aspiration de la couche limite. Cette méthode repose sur une stratégie d’aspiration en deux étapes. Dans un premier temps, un contrôle passif, par courbure et diffusion, de la position du point de décollement est effectué dans le but de la rendre insensible aux conditions de fonctionnement. Dans un second temps, un contrôle actif par aspiration vise à placer la fente d’aspiration par rapport au point de décollement de manière à minimiser le taux d’aspiration nécessaire au recollement de la couche limite. Afin de mettre en pratique cette stratégie, une technique de dessin d’aubages par prescription de la distribution de courbure de l’extrados et de la variation de section du canal inter-aubes, est ainsi développée. Associée à un outil de pré-dimensionnement rapide ainsi qu’une évaluation des pertes de pression totale incluant la présence d’aspiration, cette méthode permet ainsi de concevoir une grille de stator aspirée subsonique réalisant une déflexion fluide de 60 degrés, pour un nombre de Mach amont de 0,5, correspondant à un facteur de diffusion de 0,73. Cette performance au point nominal est obtenue avec un coefficient de pertes de pression totale de 2,5%, en aspirant 1,1% du débit entrant dans la grille. Ces valeurs peuvent néanmoins être réduites respectivement à 2,1% et 0,8% par l’emploi d’une fente d’aspiration à bords arrondis. Cette étude numérique bidimensionnelle est effectuée à l’aide du code de calcul elsA de l’ONERA. Afin de valider expérimentalement cette méthode de conception ainsi que les outils numériques associés, une grille d’aubes plane est construite et testée à basse vitesse au laboratoire de Mécanique de Fluides et d’Acoustique de l’Ecole Centrale de Lyon. A mi-envergure, les résultats issus de l’expérience et de simulations numériques 3D confirment la pertinence de la stratégie d’aspiration et la démarche de conception adoptée. Cette confrontation met alors en évidence l’impact de la distribution du taux d’aspiration suivant l’envergure sur l’efficacité de l’aspiration. Etant donné l’importance des écoulements tridimensionnels rencontrés, une généralisation en trois dimensions de la stratégie d’aspiration est proposée et est appliquée numériquement sur cette même grille d’aubes. En contrôlant simultanément les couches limites se développant sur l’aube et sur les parois latérales du canal de compression, il est alors possible de supprimer presque totalement les décollements de coins présents dans celui-ci. En contrepartie, le taux d’aspiration voit sa valeur augmenter très fortement, tempérant ce bénéfice. L’épaisseur des couches limites entrantes se révèle alors également être un facteur déterminant pour le succès du contrôle des couches limites par aspiration, dans un cadre tridimensionnel. / In order to reduce the mass of aircraft jet engines as well as their fuel consumption, manufacturers tend to make the compression system of their engines more compact, since this component represents approximately 40% of the total mass. However, for a given overall pressure ratio, decreasing the number of stages implies increasing the aerodynamic load per stage. This all the more increases the risk of flow separation on the blades ultimately resulting in a decrease in performance. Boundary layer suction on the blade has proven to be very promising to suppress this deleterious flow separation and meet the needs of high aerodynamic loads. Nevertheless, boundary layer suction significantly modifies the static pressure distribution on the blades, making traditional design approaches unsuitable. Therefore, the objective of this Ph.D. work is to develop a new method and new criteria for the design of highly loaded compressor blades, integrating boundary layer suction into the design process. This design method relies on a two-step aspiration strategy. First, passive control of the separation point location is applied via curvature and diffusion in order to make it insensitive to operating conditions. Second, active control through boundary layer suction aims at placing the suction slot with respect to the separation point location, in order to minimize the necessary suction mass flow rate required to reattach the flow. To put this strategy into practice, a blading technique that consists of prescribing the curvature distribution on the suction side of the blade and the cross-section distribution of the blade passage is developed. In association with a fast pre-design tool, as well as an overall total pressure loss coefficient including aspiration, this method allows the design of a subsonic aspirated stator cascade with flow turning of 60 degrees, for an inlet Mach number of 0.5,giving a Diffusion Factor of 0.73. This performance at the design point is obtained for an overall total pressure loss coefficient of 2.5%, aspirating 1.1% of the inlet mass flow rate. Nevertheless, these two values can be respectively reduced to 2.1% and 0.8% by rounding the edges of the suction slot. This bi-dimensional numerical study has been carried out with the elsA solver from ONERA. To experimentally validate this design method and the associated numerical tools, a planar cascade is built and tested at low speed at the Laboratoire de Mécanique de Fluides et d’Acoustique at the Ecole Centrale de Lyon. At mid-span, results from the experiment and from tri-dimensional numerical simulations confirm the relevance of the design approach. This comparison then discloses the impact of the suction mass flow rate distribution along the span, on the efficiency of aspiration. Given the importance of tri-dimensional flows encountered in the experiment and simulations, a generalization in three dimensions of the aspiration strategy is proposed and numerically applied on the same cascade. By simultaneously controlling the boundary layers developing on the blades and on the endwalls,it is possible to almost entirely suppress the corner separations present in the blade passage. However, one disadvantage is that the suction mass flow rate undergoes a strong increase, moderating this benefit. The thickness of the inlet boundary layers appears to be also a key factor in the success of boundary layer control by aspiration, in a tri-dimensional context.

Les pompiers méditerranéens sont confrontés à des embrasements soudains de la végétation (AFF) dont les mécanismes ne sont pas encore bien compris. La végétation étant l'unique combustible, nous nous sommes penchés sur les gaz qui en proviennent. Nous avons d’abord étudié la dégradation thermique de quatre Composés Organiques Volatils biogéniques (COVb) à l'aide d'une pyrolyse flash et d'un four tubulaire. À partir de cette étude et de la littérature, nous avons choisi un mélange d'étude afin expérimenter ses propriétés de combustion. Nous avons ainsi déterminé l'Énergie Minimale d’Inflammation (EMI) et la vitesse fondamentale de flamme de mélanges d'α-pinène/benzène qui sont respectivement les principaux COV détectés dans les plantes et dans les fumées de feux de forêt. Le dernier chapitre concerne l'étude stationnaire de l'accumulation de gaz dans des vallées à partir d'une maquette de forêt 1/400ème disposée dans une soufflerie. / Mediterranean firefighters cope with powerful accelerations of forest fires (AFF) whose mechanisms are not very well understood. Vegetation is the only fuel of forest fire, then we studied the gases coming from them. First, we studied the thermal degradation of four Biogenic Volatil Organic Compounds (BVOCs) thanks to a flash pyrolysis and a tubular oven. From this study and literature, we chose a representative VOC mixture to study its combustion properties. We determined Minimal Ignition Energy (MIE) and its laminar burning speed of mixtures of α-pinene/benzene that are respectively the main VOC detected in vegetation and forest fire smoke. The last chapter experiment the steady-state gas accumulation above a 1/400 V-shaped forest model.