Evaluating aerodynamic noise from aircraft engines is a design stage process, so that it conform to regulations at airports. Aerodynamic noise is also a principal source of structural vibration and internal noise in short/vertical take off and landing and rocket launches. Acoustic loads may be critical for the proper functioning of electronic and mechanical components. It is imperative to have tools with capability to predict noise generation from turbulent flows. Understanding the mechanism of noise generation is essential in identifying methods for noise reduction. Lighthill (1952) and Lighthill (1954) provided the first explanation for the mechanism of aerodynamic noise generation and a procedure to estimate the radiated sound field. Many such procedures, known as acoustic analogies are used for estimating the radiated sound field in terms of the turbulent fluid flow properties. In these methods, the governing equations of the fluid flow are rearranged into two parts, the acoustic sources and the propagation terms. The noise source terms and propagation terms are different in different approaches. A good description of the turbulent flow field and the noise sources is required to understand the mechanism of noise generation. Computational aeroacoustics (CAA) tools are used to calculate the radiated far field noise. The inputs to the CAA tools are results from CFD simulations which provide details of the turbulent flow field and noise sources. Reynolds-Averaged Navier Stokes (RANS) solutions can be used as inputs to CAA tools which require only time-averaged mean quantities. The output of such tools will also be mean quantities. While complete unsteady turbulent flow details can be obtained from Direct Numerical Simulation (DNS), the computation is limited to low or moderate Reynolds number flows. Large eddy simulations (LES) provide accurate description for the dynamics of a range of large scales. Most of the kinetic energy in a turbulent flow is accounted by the large-scale structures. It is also the large-scale structures which accounts for the maximum contribution towards the radiated sound field. The results from LES can be used as an input to a suitable CAA tool to calculate the sound field. Numerical prediction of turbulent flow field, the acoustic sources and the radiated sound field is at the focus of this study. LES based on explicit filtering method is used for the simulations. The method uses a low-pass compact filter to account for the sub-grid scale effects. A one-parameter fourth-order compact filter scheme from Lele (1992) is used for this purpose. LES has been carried out for four different flow situations: (i) round jet (ii) plane jet (iii) impinging round jet and (iv) impinging plane jet. LES has been used to calculate the unsteady flow evolution of these cases and the Lighthill’s acoustic sources. A compact difference scheme proposed by Hixon & Turkel (1998) which involves only bi-diagonal matrices are used for evaluating spatial derivatives. The scheme provides similar spectral resolution as standard tridiagonal compact schemes for the first spatial derivatives. The scheme is computationally less intensive as it involves only bi-diagonal matrices. Also, the scheme employs only a two-point stencil. To calculate the radiated sound field, the Helmholtz equation is solved using the Green’s function approach, in the form of the Kirchhoff-Helmholtz integral. The integral is performed over a surface which is present entirely in the linear region and covers the volume where acoustic sources are present. The time series data of pressure and the normal component of the pressure gradient on the surface are obtained from the CFD results. The Fourier transforms of the time series of pressure and pressure gradient are then calculated and are used as input for the Kirchhoff-Helmholtz integral. The flow evolution for free jets is characterised by the growth of the instability waves in the shear layer which then rolls up into large vortices. These large vortical structures then break down into smaller ones in a cascade which are convected downstream with the flow. The rms values of the Lighthill’s acoustic sources showed that the sources are located mainly at regions immediately downstream of jet break down. This corresponds to the large scale structures at break down. The radiated sound field from free jets contains two components of noise from the large scales and from the small scales. The large structures are the dominant source for the radiated sound field. The contribution from the large structures is directional, mainly at small angles to the downstream direction. To account for the difference in jet core length, the far field SPL are calculated at points suitably shifted based on the jet core length. The peak value for the radiated sound field occurs between 30°and 35°as reported in literature. Convection of acoustic sources causes the radiated sound field to be altered due to Doppler effect. Lighthills sources along the shear layer were examined in the form of (x, t) plots and phase velocity pattern in (ω, k) plots to analyse for their convective speeds. These revealed that there is no unique convective speeds for the acoustic sources. The median convective velocity Uc of the acoustic sources in the shear layer is proportional to the jet velocity Uj at the center of the nozzle as Uc ≈ 0.6Uj. Simulations of the round jet at Mach number 0.9 were used for validating the LES approach. Five different cases of the round jet were used to understand the effect of Reynolds number and inflow perturbation on the flow, acoustic sources and the radiated sound field. Simulations were carried out for an Euler and LES at Reynolds number 3600 and 88000 at two different inflow perturbations. The LES results for the mean flow field, turbulence profiles and SPL directivity were compared with DNS of Freund (2001) and experimental data available in literature. The LES results showed that an increase in inflow forcing and higher Reynolds number caused the jet core length to reduce. The turbulent energy spectra showed that the energy content in smaller scale is higher for higher Reynolds number. LES of plane jets were carried out for two different cases, one with a co-flow and one without co-flow. LES of plane jets were carried out to understand the effect of co-flow on the sound field. The plane jets were of Mach number 0.5 and Reynolds number of 3000 based on center-line velocity excess at the nozzle. This is similar to the DNS by Stanley et al. (2002). It was identified that the co-flow leads to a reduction in turbulence levels. This was also corroborated by the turbulent energy spectrum plots. The far field radiation for the case without co-flow is higher over all angles. The contribution from the low frequencies is directional, mainly towards the downstream direction. The range of dominant convective velocities of the acoustic sources were different along shear layers and center-line. The plane jet results were also used to bring out a qualitative comparison of flow and the radiation characteristics with round jets. For the round jet, the center-line velocity decays linearly with the stream-wise distance. In the plane jet case, it is the square of the center-line velocity excess which decays linearly with the stream-wise distance. The turbulence levels at any section scales with the center-line stream-wise velocity. The decay of turbulence level is slower for the plane jet and hence the acoustic sources are present for longer distance along the downstream direction. Subsonic impinging jets are composed of four regions, the jet core, the fully developed jet, the impingement zone and the wall jet. The presence of the second region (fully developed free jet) depends on the distance of the wall from the nozzle and the length of the jet core. In impinging jets, reflection from the wall and the wall jet are additional sources of noise compared to the free jets. The results are analysed for the contribution of the different regions of the flow towards the radiated sound field. LES simulations of impinging round jets and impinging plane jet were carried out for this purpose. In addition, the results have been compared with equivalent free jets. The directivity plots showed that the SPL levels are significantly higher for the impinging jets at all angles. For free jets, a typical time scale for the acoustic sources is the ratio of the nozzle size to the jet velocity. This is ro/Uj for round jets and h/Uj for plane jets. For impinging jets, the non-dimensionlised rms of Lighthill’s source indicates that the time scale for acoustic sources is the ratio of the height of the nozzle from the wall to the jet velocity be L/Uj. LES of impinging round jets was carried out for two cases with different inflow perturbations. The jets were at Reynolds number of 88000 and Mach number of 0.9, same as the free jet cases. The impingement wall was at a distance L = 24ro from the nozzle exit. For impinging round jets, the SPL levels are found to be higher than the equivalent free jets. From the SPL levels and radiated noise spectra it was shown that the contribution from the large scale structures and its reflection from the wall is directional and at small angles to the wall normal. The difference in the range of angles where the radiation from the large scale structures were observed shows the significance of refraction of sound waves inside the flow. The rms values of the Lighthill’s sources indicate two dominant regions for the sources, just downstream of jet breakdown and in the impingement zone. The LES of impinging plane jet was done for a jet of Mach number 0.5 and Reynolds number of 6000. The impingement wall was at a distance L = 10h from the nozzle exit. The radiated sound field appears to emanate from this impingement zone. The directivity and the spectrum plots of the far field SPL indicate that there is no preferred direction of radiation from the impingement zone. The Lighthill’s sources are concentrated mainly in the impingement zone. The rms values of the sources indicate that the peak values occur in the impingement zone. The results from the different flow situations demonstrates the capability of LES with explicit filtering method in predicting the turbulent flow and radiated noise field. The method is robust and has been successfully used for moderate Reynolds number and an Euler simulation. An important feature is that LES can be used to identify acoustic sources and its convective speeds. It has been shown that the Lighthill source calculations, the calculated sound field and the observed radiation patterns agree well. An explanation for these based on the different turbulent flow structures has also been provided.

Advances in electronics fabrication, coupled with the demand for increased computing power, have driven the demand for innovative cooling solutions to dissipate waste heat generated by these devices. To meet future demands, research and development has focused on robust and stable two-phase heat transfer devices. A confined impinging jet is explored as means of utilizing two-phase heat transfer while minimizing flow instabilities observed in microchannel devices. The test configuration consists of a 4 mm diameter jet of water that impinges on a 38 mm diameter heated aluminum surface. Experimental parameters include inlet mass flow rates from 150 to 600 g/min, nozzle-to-surface spacing from 1 to 8 mm, and input heat fluxes from 0 to 90 W/cm2. Results were used to assess the influence of the testing parameters on the heat transfer performance and stability characteristics of a two-phase confined impinging jet. Stability characteristics were explored using power spectral densities (PSDs) of the inlet pressure time series data. Confined impinging jets, over the range of conditions tested, were found to be stable and an efficient means of removing large amounts of waste heat. The radial geometry of the confined jet allows the fluid to expand as it flows radially away from the nozzle, which suppresses instabilities found in microchannel array geometries. Conditions of the heater surface were found to strongly influence two-phase performance. Analysis of PSDs, for stable operation, showed dominate frequencies in the range of 1-4 Hz, which were attributed to generated vapor expanding in the outlet plenum and the subsequent collapse as it condensed. A stability indicator was developed by inducing artificial instabilities into the system by varying the amount of cross sectional area available for outlet vapor removal and compared to the results for stable operation. / Graduation date: 2012

The homogeneous charge compression ignition (HCCI) concept has been acknowledged as a potential combustion concept for engines, due to low NOx and soot emissions and high efficiency, especially at part-load. Early direct-injection (DI) during the compression stroke is an option when Diesel fuel is used in HCCI. This implies that the risk for wall impingement increases, due to the decreasing in-cylinder density. The fuel sprays has to be well dispersed in order to avoid wall impingement. Specially designed impinging nozzles providing a collision of the Diesel sprays in the vicinity of the orifice exits have experimentally been verified to yield well dispersed sprays and the desired benefits of HCCI under various conditions. The purpose of this work is to use Computational Fluid Dynamics (CFD) as a tool to simulate and evaluate non-impinging and impinging nozzles with respect to mixture formation in direct-injected HCCI. Three different nozzles are considered: one non-impinging and two impinging nozzles with 30 and 60 degree collision angle respectively. Lagrangian CFD simulations of impinging sprays using the traditional collision model of O’Rourke is not sufficient in order obtain the correct spray properties of impinging sprays. This work proposes an enhanced collision model, which is an extension of the O’Rourke model with respect to collision frequency, post collisional velocities and collision induced break-up. The enhanced model is referred to as the EORIS model (Enhanced O’Rourke model for Impinging Sprays). The initial drop size distribution at orifice and break-up time constant of the standard Wave model is calibrated and calculated wall impingement (piston and liner) is compared with combustion efficiency, smoke, HC and CO emissions as a function of injection timing. A set of model parameters were selected for further evaluation. These model parameters and the EORIS collision model were applied to non-impinging and impinging nozzles under low- and high load conditions. The EORIS model and the selected model parameters are able to predict wall impingement in agreement with experimental measurements of combustion efficiency and smoke emissions under low- and high load conditions for the investigated nozzles. A benefit is that one set of model parameters can be used to predict mixture formation, and there is no need for additional model calibration when, for instance, the injection timing or nozzle geometry is changed. In general, experiments and simulations indicate that impinging nozzles are recommended for early injection timing in the compression stroke. This is due to the shorter penetration which leads to a reduced risk for wall impingement. The non-impinging nozzles are, however, beneficial for later injection timing in the compression stroke. During these injection conditions the impinging nozzles have a more stratified charge and under some conditions poor mixture quality is achieved. / HCCI-konceptet (Homogeneous Charge Compression Ignition) är en tänkbar förbränningsprincip för att uppnå låga NOx och sotemissioner, speciellt under låglast förhållanden. Då Diesel används som bränsle är tidig direktinsprutning under kompressionsslaget en tänkbar strategi för att åstadkomma gynnsamma HCCI-förhållanden. Den tidiga direktinsprutningen medför däremot att risken för väggvätning ökar, på grund av den minskade densiteten i cylindern. Detta ställer krav på bränslesprejen som måste vara väl fördelad i cylindern för att undvika väggvätning. Specialkonstruerade spridarspetsar som skapar kollision av sprejerna nära hålmynningen, så kallade kolliderande sprejer, har experimentellt påvisats vara fördelaktiga för HCCI förbränning, tack vare kortare sprejpenetration och voluminös sprej. Syftet med detta arbete är att använda CFD (Computational FluidDynamics) som ett verktyg för att simulera och evaluera ickekolliderande och kolliderande sprejer med avseende på blandningsbildning under direktinsprutade HCCI förhållanden. Tre olika spridarspetsar har undersökts: en icke-kolliderande och två kolliderande med kollisionsvinkel 30 och 60 grader. CFD-simuleringar av kolliderande sprejer med Lagrangiansk modelleringsteknik och O’Rourkes traditionella kollisionsmodell har visat sig vara otillräcklig för att uppnå korrekta sprejegenskaper. Den här avhandlingen presenterar en förbättrad kollisionsmodell baserad på O’Rourkes ursprungliga kollisionsmodell med avseende på kollisionsfrekvens, dropphastighet efter kollision och kollisionsviinducerad break-up. Den förbättrade modellen kallas EORIS (Enhanced O’Rourke model for Impinging Sprays). Den initiala droppfördelningen vid spridarspetsens hålmynning och Wave-modellens tidskonstant för break-up har kalibrerats och beräknad väggvätning (kolv och foder) har jämförts med förbränningsverkningsgrad, rök, HC och CO-emissioner som funktion av insprutningstidpunkt. De valda modellparametrarna och EORIS-modellen tillämpades för att evaluera blandningsbildningen på kolliderande och icke-kolliderande spridarspetsar under låg- och höglast-förhållanden. EORIS-modellen och de utvalda modellparametrarna kan predikteraväggvätning i överensstämmelse med uppmätt förbränningsverkningsgrad och rökemissioner under låglast- och höglastförhållanden för de undersökta spridarspetsarna. En fördel är att de utvalda modellparametrarna kan prediktera blandningsbildningen och det finns inget behov att justera modellparametrarna då t.ex. insprutningstidpunkten eller spridarspetsgeometrin ändras. Generellt påvisar såväl experiment som simuleringar att de kolliderande sprejerna är lämpliga för tidig direktinsprutning underkompressionsslaget. Det är på grund av kort sprejpenetration som reducerar risken för väggvätning. De icke-kolliderande sprejerna är dock lämpliga för sen direktinsprutning under kompressionsslaget. Under dessa förhållanden har de kolliderande sprejerna en mer stratifierad blandning och under vissa förhållanden uppnås då en ofördelaktig blandningskvalitet. / QC 20100819

This thesis deals with Large Eddy Simulation (LES) of impinging air jets. The impinging jet configuration features heated circular jets impinging onto a flat plate. The problem addressed here is of generic nature, with applications in many engineering devices, such as cooling of components in gas turbines, in cars and electronic devices. The flow is inherently unsteady and contains relatively slowly varying coherent structures. Therefore, LES is the method of choice when the Reynolds number is large enough to exclude Direct Numerical Simulations (DNS). The present LES model is a basic model without explicit Sub-Grid-Scale (SGS) modeling and without explicit filtering. Instead, the numerical scheme is used to account for the necessary amount of dissipation. By using the computational grid as a filter the cutoff wavenumber depends explicitly on the grid spacing. The underlying computational grid is staggered and constructed in a Cartesian coordinate system. Heat transfer is modeled by the transport equation for a passive scalar. This is possible due to the negligible influence of buoyancy which implies constant density throughout the flow field. The present method provides accurate results for simple geometries in an efficient manner. A great variety of inlet conditions have been considered in order to elucidate how the dynamics of the flow and heat transfer are affected. The considered studies include top-hat and mollified mean velocity profiles subjected to random and sinusoidal perturbations and top-hat profiles superimposed with solid body rotation. It has been found that the shape of the mean inlet velocity profile has a decisive influence on the development of the flow and scalar fields, whereas the characteristics of the imposed artificial disturbances (under consideration) have somewhat weaker effect. In order to obtain results unequivocally comparable to experimental data on turbulent impinging jets both space and time correlations of the inflow data must be considered, so also the spectral content. This is particularly important if the region of interest is close to the velocity inlet, i.e. for small nozzle-to-plate spacings. Within this work mainly small nozzle-toplate spacings are considered (within the range of 0.25 and 4 nozzle diameters), which emphasizes the importance of the inflow conditions. Thus, additional to the basic methods also turbulent inflow conditions, acquired from a precursor pipe simulation, have been examined. Both for swirling and non-swirling flows. This method emulates fully developed turbulent pipe flow conditions and is the best in the sense of being well defined, but it demands a great deal of computing power and is also rather inflexibility. In case of the basic randomly perturbed methods the top-hat approach has been found to produce results in closest agreement with those originating from turbulent inlet conditions. In the present simulations the growth of individual instability modes is clearly detected. The character of the instability is strongly influenced by the imposed boundary conditions. Due to the lack of correlation random superimposed fluctuations have only a weak influence on the developing flow field. The shape of the mean profile, on the other hand, influences both the growth rate and the frequency of the dominant modes. The top-hat profile yields a higher natural frequency than the mollified. Furthermore, for the top-hat profile coalescence of pairs of vortices takes place within the shear-layer of the axial jet, whereas for the mollified profile (for the considered degree of mollification) it takes place within the wall jet. This indicates that the transition process is delayed for smoother profiles. The amount of wall heat transfer is directly influenced by the character of the convective vortical structures. For the mollified cases wall heat transfer originates predominantly from the dynamics of discrete coherent structures. The influence from eddy structures is low and hence Reynolds analogy is applicable, at least in regions of attached flow. The top-hat and the turbulent inflow conditions yield a higher rate of incoherent small scale structures. This strongly affects the character of wall heat transfer. Also the applied level of swirl at the velocity inlet has significant influence on the rate of heat transfer. The turbulence level increases with swirl, which is positive for heat transfer, and so also the spreading of the jet. The latter effect has a negative influence on wall heat transfer, particularly in the center most regions. This however depends also on the details of the inflow data. / QC 20100831

The basis of mixing ventilation is the airflow supply to the room by means of jets initiatedfrom the ventilation diffusers. To avoid the draught problem, the design of mixing ventilationmakes uses the throw term, which is defined as the distance to the supply air terminal inwhich the jet centreline mean velocity is decreased to a given value. Traditionally, the throw ismeasured by the supply air device manufacturer. The throw is applied by designers to estimatethe velocity levels in the occupied zone. A standard for determining the throw is the CENstandard CEN/TC156/WG4 N86 "Draft Standard. Air terminal Devices. AerodynamicsTesting And Rating For Mixed Flow Application".The measurement of the throw is very time consuming even with the free jets and theinfluence of the room (the effect of confinement) is not considered. The objective of thepresent study is to give a basis for modifying the existing design and testing method used topredict the velocities in the occupied zone during the design process. A new method whichmay probably be more easier than the existing methods and at the same time give a betterprecision by including the confinement effect.In this thesis two methodological systems of experiment and numerical simulations have beenused. The numerical predictions are used in comparison with the measurements. Thereasonable agreement of the above mentioned methods is implemented to numerical study ofthe other room configurations which are not experimentally studied. This examining methodallows the possibility of studying a lot of configurations and in this manner generalising of theresults. Although the experimental part was made for both model-scale and full-scale testrooms, a large amount of data was obtained for a new test room whose dimension aresystematically varied. All of studies have been made for the isothermal case and themeasurements of velocities and pressures conducted along the room perimeters. The effect ofshort and deep rooms on the properties of the jet ( velocities, pressure, integral scale, jetmomentum, the rate of spreading of jet and turbulence intensities) have been carried out.Some old and recent investigations have been examined. Specially the concept of correlationsfrom open to closed rooms is criticised. It is also shown that the flow field in a confined roomis affected by many other factors than the Reynolds number. The surface pressure on theperimeters was used to calculate the reaction forces at the corners which causes recirculatingbubbles at corners. A study of the turbulent axisymmetric jet which is the basic element inturbulent shear flows and some restrictions of the traditional measurement techniques at theregion of interest in ventilation applications are discussed. The jet momentum is measured byweighing on a balance. Also a study of jets which collide with a wall , that is impinging jet,the effect of walls and confinement on the jet momentum have experimentally andnumerically been carried out. A new momentum balance model was developed for both thefree jet and confined one. An empirical relation has been found for estimation of the room’srotation centre which is used for validation of CFD results.Finally, it is found that the jets in a ventilated room which are a combination of free jet, walljet and impinging jet differ from the traditional wall jets. The rate of spreading of the jet andthe maximum velocity decay in a ventilated room are also different depending on the roomsize and its confinement.

Les mécanismes élémentaires mis en jeu lors de l’érosion de surface d’un sol cohésif par un écoulement fluide demandent à être mieux connus dans le but d’améliorer la modélisation locale de l’érosion. En se basant sur une approche expérimentale, l’objectif de cette thèse vise à réaliser une étude paramétrique de l'érosion à l'aide de matériaux modèles, pour ensuite les soumettre à des sollicitations hydrodynamiques et mécaniques contrôlées. L'étude de matériaux granulaire sans cohésion a d'abord permis d'analyser la construction du nombre de Shields pour définir le seuil d'érosion. Ensuite, des essais de traction à différentes échelles ont permis de généraliser le nombre de Shields à des grains cohésifs par la relation entre seuil d'érosion et résistance mécanique. La mise au point de matériaux et d'essais d'érosion iso-indice a également permis de visualiser les mécanismes par lesquels l'écoulement conduit à l’arrachement de particules constitutives du matériau modèle lors d'essais de JET et de HET. Pour finir, d'autres types de matériaux cohésifs modèles ont été plus rapidement étudiés et révèlent de grandes perspectives d'études. / Elementary mechanisms involved during the surface erosion of a cohesive soil by a fluid flow ask to be better understood for improving the local modeling of erosion. It is the objective of this thesis which aims, by an experimental approach, at working out model materials to submit them to hydrodynamic stresses and controlled mechanic stresses. The study of cohesion-less granular material allowed, in a first approach, to analyse the Shields number formulation to define the erosion threshold. In a second time, the grains have been made cohesive with liquid or solid matrix, and mechanical tests at different scales allowed to generalise the Shields number to both cohesive and non-cohesive particles. The development of erosion tests adjusted in optical index also made possible to visualised the mechanisms by which the fluid flow erode the constitutive particles of the material during Jet Erosion Tests and Hole Erosion Tests. Finally, different kinds of cohesive model materials were tested and show excellent perspectives.

No description available.

With the continuous growth of the space industry and the introduction of reusable rockets, the number of rocket launches is expected to increase significantly in the following years. During rocket launching, the engine exhaust impinges on the launch structure producing a complex flow field. The rocket jet induces large thermoaerodynamic and acoustic loads on the launch structures and the rocket. This thesis aims to study the physics and numerical considerations behind supersonic flows exhausted from rocket engines. First, the treatment of turbulent compressible flows through the Favre-averaged equations and the SST k-ω model are studied. Next, the numerical modeling of the problem, including solver and meshing theory is presented. Then, a model of a nozzle is explained along with how the performance is assessed to finally design a M=3 two-dimensional nozzle using the method of characteristics (MOC). The two-dimensional results are validated using Ansys Fluent, and the same geometry is used for the following axisymmetrical problems, which include the study of a free and impinging jet. The free jet problem serves to study how the nozzle behaves in a two-dimensional axisymmetric problem and to validate the impinging jet results. To obtain the results, RANS-based simulations of a cold, over-expanded jet with adiabatic walls are performed. Empirical formulas were used to verify the results. Lastly, the impinging jet problem is simulated using the same inlet boundary conditions as for the free jet. The impact that the plate distance to the exit of the nozzle has on the position of the shock waves when the jet impinges on the flat surface is assessed. Finally, an optimization of the shape of a wedge to minimize the maximum turbulence kinetic energy produced during steady-state simulation is carried out. As an appendix to the work, an aeroacoustic study of the impinging jet at 4De distance is presented. The results show the direction of propagation of the acoustic waves but due to the lack of acoustic quality of the mesh, the predicted sound pressure levels do not match the expected behavior.

Le présent manuscrit de thèse présente l'étude de différents phénomènes dans un convertisseur d?acier, grâce au développement de deux modèles distincts. Le premier modèle décrit la cavité produite à la surface libre du bain de métal par l'impact du jet d'oxygène supersonique. Il est basé sur le découpage du domaine de calcul en deux régions. Les effets de compressibilité du gaz sont pris en compte uniquement dans la région du jet où la vitesse est élevée, alors que partout ailleurs, le gaz est considéré comme incompressible. La méthode Volume Of Fluid (VOF) est utilisée pour suivre la déformation de la surface libre du bain. Les résultats de simulations sont présentés pour des systèmes bi- et triphasés et comparés à des données expérimentales obtenues dans diverses maquettes froides. L'influence sur la taille et la forme de la cavité de différents paramètres (parmi lesquels les conditions aux limites en sortie de la lance d'injection, le schéma d'advection de la méthode VOF et le modèle de turbulence) est étudiée. Le modèle est ensuite utilisé pour simuler l'interaction entre un jet supersonique d'oxygène et la surface libre d'un bain d'acier liquide dans un convertisseur de taille pilote. Le second modèle se focalise sur l'écoulement du gaz, le transfert de chaleur et la réaction de postcombustion dans la phase gazeuse au-dessus du bain de métal. Il utilise l'algorithme Simple Chemical Reaction Scheme pour décrire le transport des espèces chimiques, et prend en compte l'absorption d'oxygène dans le bain et les transferts thermiques par rayonnement. Les prédictions numériques sont en assez bon accord avec les mesures recueillies dans une expérience de laboratoire et dans un four à l'échelle pilote / The present thesis treats different phenomena taking place in a steelmaking converter through the development of two separate models. The first model describes the cavity produced at the free surface of the metal bath by the high speed impinging oxygen jet. It is based on a zonal approach, where gas compressibility effects are taken into account only in the high velocity jet region while elsewhere the gas is treated as incompressible. The Volume Of Fluid (VOF) method is employed to follow the deformation of the bath free surface. Calculations are presented for two- and three-phase systems and compared against experimental data obtained in various cold model experiments. The influence on the size and shape of the cavity of various parameters (including the jet inlet boundary conditions, the VOF advection scheme and the turbulence modelling) is studied. Next, the model is used to simulate the interaction of a supersonic oxygen jet with the surface of a liquid steel bath in a pilot-scale converter. The second model concentrates on fluid flow, heat transfer and the post-combustion reaction in the gas phase above the metal bath. It uses the Simple Chemical Reaction Scheme approach to describe the transport of the chemical species and takes into account the consumption of oxygen by the bath and thermal radiative transfer. The numerical predictions are in reasonable agreement with measurements collected in a laboratory experiment and in a pilot-scale furnace

Les systèmes de climatisation et de ventilation sont souvent composés de configurations type jets impactant, sur leur partie terminale. Ainsi, les flux d’air soufflés viennent impacter des obstacles munis de fentes, de différentes formes, afin d’améliorer le mélange. Les conditions de confinement et de soufflage provoquent parfois un inconfort au niveau acoustique. Les nuisances acoustiques générées sont dues à un phénomène de boucles de rétroaction se traduisant par l’apparition des sons auto-entretenus. La production du son par un écoulement fluide en champ libre ou en interaction avec une structure a fait l’objet de nombreuses études. Dans le cas d’un champ acoustique et pour un écoulement à faible nombre de Mach la résolution du corollaire énergétique de Howe permet d’évaluer la puissance acoustique générée ou absorbée par les interactions entre le champ acoustique et l’écoulement. Le calcul de cette puissance nécessite la connaissance de trois paramètres : la vorticité, la vitesse et la vitesse acoustique par des méthodes analytiques ou en utilisant des données expérimentales. Expérimentalement, la mesure du champ cinématique, pour en déduire la vorticité, nécessite une technique de mesure tridimensionnelle. Pour cela une plate-forme expérimentale, utilisant de la vélocimétrie Laser, a été développée, et équipée pour générer les écoulements d’un jet plan. Les champs cinématiques de ces écoulements ont été mesurés en utilisant la technique PIV, avec un dispositif de PIV stéréoscopique. Les champs cinématiques de trente plans parallèles ont été mesurés afin d’étudier les champs de vitesses correspondants. Deux méthodes de reconstruction ont été appliquées à ces plans : la POD et la moyenne de phase. Le volume est obtenu par une interpolation des plans reconstruits donnant accès aux trois composantes de la vitesse. Pour valider ces méthodes de reconstruction en 3D à faible coût, elles étaient comparées à des mesures expérimentales réalisées par le même dispositif expérimental, dans les mêmes conditions, par la PIV tomographique donnant accès aux champs cinématiques tridimensionnels. / Air conditioning and ventilation systems are often composed of jets having a configuration of an impinging jet, on their end part. Thus, the blown airflows impact slotted obstacles of different shapes to improve mixing. The conditions of confinement and blowing sometimes cause acoustic incompatibility. The acoustic noises generated are due to a phenomenon of feedback loops resulting of the appearance of self-sustained sounds. The production of sound by a free flow or in interaction with a structure has been the subject of many studies. In the case of an acoustic field and for a flow of low Mach number, Howe's energetic correlation is used to evaluate the acoustic power generated or absorbed by the interactions between the acoustic field and the flow. The calculation of this power requires the knowledge of three parameters : vorticity, velocity and acoustic velocity by analytical methods or by using experimental data. Experimentally, the measurement of the kinematic field, to deduce the vorticity, requires a three-dimensional measurement technique. For this purpose, an experimental platform, using laser velocimetry, has been developed and equipped to generate flows of a plane jet. The kinematic fields of these flows were measured using the PIV technique, with a stereoscopic PIV device. The kinematic fields of thirty parallel planes were measured to study the corresponding velocity fields. Two reconstruction methods have been applied to these plans : the POD and the phase average. The volume is obtained by an interpolation of the reconstructed planes giving access to the three components of the velocity. To validate these low-cost 3D reconstruction methods, they were compared to experimental measurements made by the same experimental setup, under the same conditions, by using the tomographic PIV giving access to the three-dimensional kinematic fields.