Planetary ball milling (PBM) is a well-known technique for efficient size reduction and homogenization of materials that has been used for many decades in various engineering and industrial processes. More recently, it has emerged as a unique top-down nanofabrication approach for nanomaterials based on nanoscale grinding. However, its potential application in nanostructured thin film fabrication has not been fully explored, as only a limited number of studies have been carried out. In this work, the effects of different grinding parameters (speed, time and solvents) were used to create previously unstudied nanoscale grinding conditions for nanostructured thin film materials via PBM with distinct and novel properties: Nanoparticles of silicon, titanium disilicide (TiSi2) and zinc oxide (ZnO) ground in different solvents (deionized (DI) water/ ethylene glycol (EG)/isopropyl alcohol) resulted in colloidal suspensions (or nanoinks) that could be used to coat various substrates (wafers, glass, flexible substrates, etc.) via drop casting, doctor blading or dip coating. Thin film properties such as wettability, electrical conductivity and gas sensing behavior are studied. The fabricated thin film coating properties could be tuned depending on the combination of starting powder materials, grinding parameters and resulting nanoparticle size/geometry: The influence of surface chemistry, solvent type, particle geometry, surface roughness and defects was shown to alter the conductivity and surface wettability of the resultant films. Thus, thin films formed using PBM nanoinks allow varied and tunable properties for advanced multi-functional coatings and devices. To demonstrate the feasibility of PBM nanoinks for thin film device applications, ZnO nanoinks were used to create chemiresistive gas sensors that operate at room temperature. By varying grinding parameters (speed, time and solvent) thin film sensors with differing particle sizes and porosity were produced and tested with air/oxygen against hydrogen, argon and methane target gas species, in addition to relative humidity. Grinding speeds of up to 1000 rpm produced particle sizes and RMS thin film roughness below 100 nm, as measured by atomic force microscopy and scanning electron microscopy. Raman spectroscopy, photoluminescence and x-ray analysis confirmed the purity and structure of resulting films. The peak gas sensor response was found for grinding parameters of 400 rpm (average particle size 275 nm) and 30 minutes (average particle size 225 nm) in EG and DI water, respectively, which could be correlated to an increased film porosity and an enhanced electron concentration resulting from adsorption/desorption of oxygen ions on the surface of ZnO nanoparticles. Similarly, gas response and dynamic behavior were found to improve as the operating temperature was increased between 100 and 150 °C. These results demonstrate the use of low-cost PBM nanoinks to optimize the active materials for solution-processed thin film gas/humidity sensors that can operate at room temperature for use in environmental, medical, food packaging, laboratory, and industrial applications. Overall, the nanogrinding technique can produce large amounts of nanoparticle suspension with variable particle sizes for creating thin films with tunable properties. By adjusting grinding parameters, the nanoparticle shape/size and properties can be varied resulting in nanoparticle inks for inexpensive coatings on various substrates and for use in different applications. / Graduate

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.