Dans le cadre de la production d'électricité par énergie renouvelable, cette thèse a pour objectif de contribuer à l'amélioration des performances hydrodynamiques des hydroliennes à flux transverse conçues par HydroQuest. Pour y parvenir, deux axes d'étude principaux sont proposés. Le premier consiste à améliorer la compréhension de la performance de l'hydrolienne et de l'écoulement en son sein par voie numérique. L'influence du paramètre d'avance ainsi que celle de la solidité de l'hydrolienne sont étudiées. Les écoulements mis en jeux étant complexes, une méthode de type Simulation des Granges Échelles 3D est utilisée afin de les restituer au mieux. Le phénomène de décrochage dynamique, qui apparaît pour certains régimes de fonctionnement de l'hydrolienne, fait l'objet d'une étude à part entière sur un cas de profil oscillant.Le second axe se concentre sur les carénages de l’hydrolienne qui font l'objet d'une procédure d'optimisation numérique. Afin de pouvoir réaliser les nombreuses simulations requises en un temps réaliste, des méthodes de type Unsteady Reynolds-Averaged Navier-Stokes 2D moins coûteuses et fournissant une précision suffisante pour ce type d'étude sont utilisées. / Within the renewable electricity production framework, this study aims to contribute to the efficiency improvement of the Vertical Axis Hydrokinetic Turbines designed by HydroQuest. To achieve this objective, two approaches are used. The first consists in the improvement of the comprehension of the turbine efficiency such as the flow through the turbine by numerical means. The influence of the tip speed ratio such as the turbine soldity are investigated. The flow through the turbine is complex. A 3D Large Eddy Simulation type is thus used. The dynamic stall phenomenon which could occur in Vertical Axis Hydrokinetic Turbines is also studied in a oscillating blade configuration.The second approach consists in the numerical optimization of the turbine channeling device. To perform the high number of simulations required, a 2D Unsteady Reynolds-Averaged Navier-Stokes simulation type is used.

Le décrochage est un phénomène aérodynamique instationnaire susceptible d'apparaître sur de nombreux profils aérodynamiques. Il résulte d'un décollement important de l'écoulement vis-à-vis de la paroi de l'aile et dégrade considérablement les performances de vol. Sur certains profils de pales d'hélicoptères, d'éoliennes ou de rotors, ce phénomène se produit dans des conditions d'utilisation normales et justifie la recherche de méthodes de modélisation accessibles industriellement. Le décrochage est initié au bord d'attaque par l'apparition d'une petite région de recirculation de fluide appelée bulbe de décollement laminaire où l'écoulement transitionne de l'état laminaire vers l'état turbulent. Ce phénomène encore mal connu met en jeu transition et écoulements hors équilibre auxquels les outils de modélisation RANS habituellement employés ne sont pas adaptés. Dans cette étude, un bulbe transitionnel typique d'un écoulement de bord d'attaque de pale d'hélicoptère (profil OA209 à un nombre de Reynolds Rec∞=1.8x106 et 15° d'incidence) est isolé sur une plaque plane. Une simulation DNS de cet écoulement est réalisée à l'aide du logiciel FUNk de l'ONERA afin de servir de base de données pour l'amélioration des modèles RANS. L'évolution des bilans de l'équation de transport de l'énergie cinétique turbulente ainsi que les principales hypothèses RANS (isotropie de la turbulence, Boussinesq, équilibre production/dissipation) sont analysées. Une étude des principaux modèles RANS développés dans le logiciel elsA de l'ONERA est ensuite réalisée en pondérant les grandeurs turbulentes par une fonction de transition reproduisant l'intermittence de la turbulence. Le modèle k-ω de Wilcox couplé à une fonction de transition optimisée a donné les résultats les plus proches de la DNS et a donc été l'objet d'une analyse plus approfondie, notamment une évaluation des principales équations bilans et une application de ce modèle et de sa méthode de transition à un cas de transition naturelle de plaque plane. / The stall is an unsteady aerodynamic phenomenon that may occur on many aerodynamic profiles. It consists in a large separation of the flow from the wall of the wing and significantly deteriorates the flight performances. On some blade profiles such as helicopters, turbines or rotors, this phenomenon occurs under normal conditions of use and justifies the research of industrially accessible modeling methods. The stall is initiated at the leading edge by the appearance of a small region of fluid recirculation called a “laminar separation bubble” where the flow transitions from the laminar to the turbulent state. This still poorly understood phenomenon involves transition and non-equilibrium flows for which commonly used RANS modeling tools are not suitable. In this study, a transitional bubble typical of an helicopter leading edge flow (OA209 profile at a Reynolds number Rec∞=1.8x106 and 15° of incidence) is reproduced on a flat plate. A DNS simulation of this flow is performed using the ONERA FUNk software to serve as a database for RANS models improvements. The evolution of turbulent kinetic energy budgets as well as the main RANS assumptions (isotropy of turbulence, Boussinesq hypothesis, production/dissipation balance) are analyzed. The main RANS models developed in the ONERA elsA software are then studied by weighting the turbulent quantities with a transition function reproducing the intermittency of the turbulence. The k-ω Wilcox model coupled with an optimized transition function gave the best results and was therefore kept for a more in-depth analysis, including an assessment of the main budgets and an application of this model and its transition method to a natural transition test case on a flat plate.

A centrifugal compressor is a mechanical machine with purpose to convert kineticenergy from a rotating impeller wheel into the fluid medium by compressingit. One application involves supplying boost air pressure to downsized internalcombustion engines (ICE). This allows, for a given combustion chamber volume,more oxygen to the combustion process, which is key for an elevated energeticefficiency and reducing emissions. However, the centrifugal compressor is limitedat off-design operating conditions by the inception of flow instabilities causingrotating stall and/or surge. These instabilities appear at low flow rates andtypically leads to large vibrations and stress levels. Such instabilities affectthe operating life-time of the machine and are associated with significant noiselevels.The flow in centrifugal compressors is complex due to the presence of a widerange of temporal- and spatial-scales and flow instabilities. The success fromconverting basic technology into a working design depends on understandingthe flow instabilities at off-design operating conditions, which limit significantlythe performance of the compressor. Therefore, the thesis aims to elucidate theunderlying flow mechanisms leading to rotating stall and/or surge by means ofnumerical analysis. Such knowledge may allow improved centrifugal compressordesigns enabling them to operate more silent over a broader operating range.Centrifugal compressors may have complex shapes with a rotating partthat generate turbulent flow separation, shear-layers and wakes. These flowfeatures must be assessed if one wants to understand the interactions among theflow structures at different locations within the compressor. For high fidelityprediction of the complex flow field, the Large Eddy Simulation (LES) approachis employed, which enables capturing relevant flow-driven instabilities underoff-design conditions. The LES solution sensitivity to the grid resolution usedand to the time-step employed has been assessed. Available experimentaldata in terms of compressor performance parameters, time-averaged velocity,pressure data (time-averaged and spectra) were used for validation purposes.LES produces a substantial amount of temporal and spatial flow data. Thisnecessitates efficient post-processing and introduction of statistical averagingin order to extract useful information from the instantaneous chaotic data. Inthe thesis, flow mode decomposition techniques and statistical methods, suchas Fourier spectra analysis, Dynamic Mode Decomposition (DMD), ProperOrthogonal Decomposition (POD) and two-point correlations, respectively, areemployed. These methods allow quantifying large coherent flow structures atvfrequencies of interest. Among the main findings a dominant mode was foundassociated with surge, which is categorized as a filling and emptying processof the system as a whole. The computed LES data suggest that it is causedby substantial periodic oscillation of the impeller blade incidence flow angleleading to complete system flow reversal. The rotating stall flow mode occurringprior to surge and co-existing with it, was also captured. It shows rotating flowfeatures upstream of the impeller as well as in the diffuser. / <p>QC 20171117</p>

Floating offshore wind turbines in deep waters offer significant advantages to onshore and near-shore wind turbines. However, due to the motion of floating platforms in response to wind and wave loading, the aerodynamics are substantially more complex. Traditional aerodynamic models and design codes do not adequately account for the floating platform dynamics to assess its effect on turbine loads and performance. Turbines must therefore be over designed due to loading uncertainty and are not fully optimized for their operating conditions. Previous research at the University of Massachusetts, Amherst developed the Wake Induced Dynamics Simulator, or WInDS, a free vortex wake model of wind turbines that explicitly includes the velocity components from platform motion. WInDS rigorously accounts for the unsteady interactions between the wind turbine rotor and its wake, however, as a potential flow model, the unsteady viscous response in the blade boundary layer is neglected. To address this concern, this thesis presents the development of a Leishman-Beddoes dynamic stall model integrated into WInDS. The stand-alone dynamic stall model was validated against two-dimensional unsteady data from the OSU pitch oscillation experiments and the coupled WInDS model was validated against three-dimensional data from NREL’s UAE Phase VI campaign. WInDS with dynamic stall shows substantial improvements in load predictions for both steady and unsteady conditions over the base version of WInDS. Furthermore, use of WInDS with the dynamic stall model should provide the necessary aerodynamic model fidelity for future research and design work on floating offshore wind turbines.

To be able to harness more power from the wind, wind turbine blades are getting longer. As they get longer, they get more flexible. This creates issues that have until recently not been of concern. Long flexible wind turbine blades can lose their stability to flow induced instabilities such as coupled-mode flutter. This type of flutter occurs when increasing wind speed causes a coupling of a bending and a torsional mode, which create limit cycle oscillations that can lead to blade failure. To be able to make the design of larger blades possible, it is important to be able to predict the critical flutter and post critical flutter behaviors of wind turbine blades. Most numerical research concerning coupled-mode wind turbine is focused on predicting the critical flutter point, and less focused on the post critical behavior. This is because of the mathematical complexities associated with the coupled, nonlinear wind turbine blade systems. Here, a numerical model is presented that predicts the critical flutter velocity and post critical flutter behavior for 3D airfoils with third order structural nonlinearities. The numerical model can account for the attached flow and separated flow region by using the ONERA dynamic stall model. By retaining higher-order structural nonlinearities, lateral and torsional displacements can be predicted, which makes it possible to use this model in the future to control wind turbine blade flutter. Furthermore, by using a dynamic stall model to simulate the flow, the solver is able to predict accurate limit cycle oscillations when the effective angle of attack is larger than the stall angle. The coupled, nonlinear equations of motion are two coupled nonlinear PDEs and are determined using Hamilton’s principle. In order to solve the equations of motion, they are discretized using the Galerkin technique into a set of ODEs. The motion of the airfoil is used as an input to ONERA. The airfoil is sectioned with the lateral position and angle of attack known as well as the velocity and acceleration of the section at an instance of time. This information is used by ONERA to calculate lift and moment coefficients for each section which are then used to calculate the total lift and moment forces of the airfoil. Then, a Fortran code solves the system by using Houbolt’s finite difference method. A theoretical NACA 0012 airfoil has been designed to define the parameters used by the equations of motion. Third bending and first torsional coupling occurs after the critical flutter point and dynamic lift and moment coefficients were observed. Dynamic stall was also observed at wind velocities farther away from the bifurcation point. Bifurcation diagrams, time histories, and phase planes have been created that represent the flutter behavior.

No description available.

Kvarnängen är beläget 3,5 km norr om Nynäshamns stadskärna, omgivet av både ett stort rekreationsområde med idrottsmöjligheter i väst samt ett industriområde i öst. Tomten för Kvarnängsgården ligger i en dal, på en grusplan som tidigare var en båtuppställningsplats. De öppna fälten runt tomten används för sportaktiviteter av olika föreningar. Fram till 1960-talet var området kring Kvarnängen lantbruk med stall och gårdar. Idag är området särskilt aktivt under sommarhalvåret för utomhusaktiviteter, men det finns brist på offentliga platser att umgås på som inte är idrottsrelaterade.  På grund av den kraftiga befolkningstillväxten i Nynäshamn antas området exploateras i framtiden. Förslaget undersöker hur gårdsmiljöer kan bestå under urbanisering och vad de kan tillföra en växande stad. Kvarnängsgården vill erbjuda en tillgänglig och gemensam plats där det är möjligt för alla att ta del av Nynäshamns historia och kultur som gårdsmiljö. Detta kan i förlängningen generera hälsofrämjande aspekter för befolkningen och hjälpa kommunen att nå sina mål 11 och 12 om psykisk hälsa och tillgång till friluftsliv. Förslaget vill stärka, aktivera och tillgängliggöra kopplingen mellan stadskärnan och rekreationsområdet genom att skapa en plats att mötas på, samt att främja utbildningsnivån i kommunen. Kvarnängsgården huserar två typer av boenden: kursgårdens inackordering samt ett korttidsboende med daglig verksamhet för personer med funktionsvariation. Verksamheterna delar på lokaler som föreläsningssalar, aktivitet- och mötesrum för utbildning och interaktion, växthus, stall och restaurang vilka även kan nyttjas av allmänheten. / Kvarnängen is located 3.5 km north of Nynäshamn's city centre, surrounded by both an important recreation area with sports facilities in the west and an industrial area in the east. The site is located in a valley, on a field that was formerly a boat parking space. Due to the strong population growth in Nynäshamn, it is assumed that the location of Kvarnängen will be exploited in the future. Until the 1960s, Kvarnängen was an agricultural community with stables and farms. Today, the area is particularly active during the summer months for outdoor activities. The connection between Nynäshamn city and the recreational area is inactive for a significant portion of the year due to its lack of activated public spaces that are not related to sport. The proposal investigates how agricultural environments can persist during urbanization, and which benefits they can provide to a growing city. Kvarnängsgården wants to offer an accessible and public space where it is possible for everyone to participate in Nynäshamn's history and culture as a rural setting. Long-term, this can generate health-promoting aspects for the population and help the municipality to achieve its goals regarding mental health and equal access to outdoor activities. Kvarnängsgården seeks to strengthen and activate the connection between the city center and the leisure area by establishing a place to meet, as well as offering education and accomodation. Kvarnängsgården hybridity includes two types of accommodation: the course farm's lodging for the public and a short-term housing with daily activities for persons with certain functional impairments (according to the Swedish act of LSS). The organizations share facilities including lecture halls, activity and meeting rooms for education and interaction as well as a greenhouse, stable and restaurant, which are also open to the public.

<p>  </p> <p>The focus of this work was to characterize the overall performance effects due to altering the stagger angle of a variable inlet guide vane (VIGV) on a multistage axial compressor. Data were collected from the Purdue three-stage axial compressor (P3S). The stagger angle from the VIGV was varied thrice from the baseline configuration in increments of 5 degrees resulting in four configurations with angles of 4 deg, 9 deg, 14 deg, and 19, where the baseline configuration was 9 degrees. </p> <p>Compressor performance data were collected and analyzed for each stagger angle configuration along three corrected speeds (68%, 80%, 100%). Each speedline consisted of approximately six loading conditions for which the corrected mass flow rate was matched for each configuration to allow for a basis of comparison among the configurations. Stalling mass flow rates and stall inception were also investigated. Total pressure and total temperature rakes were installed throughout the compressor to investigate the performance at interstage locations for each loading condition. In addition to the rakes, static pressure taps were distributed along the compressor and unsteady pressure measurements were distributed circumferentially. Capacitance probes were installed over each of the three rotors to evaluate rotor tip clearance measurements during the tests. The effects of the stagger angle on the stability margin of the compressor were also characterized. Each speedline presented, thus, includes a representative stall point in addition to the six loading conditions where detailed flow field traverses were conducted. </p> <p>The results of this investigation showed that while the total pressure ratio (TPR) increased as the stagger angle decreased, the stability margin was reduced. The opposite trend was observed with a decrease in overall TPR across the compressor and an increase in stability margin for increased stagger angles. Based on findings from previous authors, this trend was anticipated. A similar metric for monitoring compressor performance is isentropic efficiency. This investigation utilized both temperature-based and torque-based isentropic efficiency. The greatest effect of the VIGV stagger angle on compressor isentropic efficiency occurred at the lowest loading conditions, and there was no discernible impact on isentropic efficiency at high loading conditions for this case. As VIGVs typically have the greatest impact on off-design conditions, this trend was expected. The varied stagger angle configurations had no discernible effect on the type of stall inception mechanism experienced by the compressor. The primary effect on stall that was consistent across the configurations was a noticeable increase in the duration and strength of modal oscillations present throughout the compressor with increased stagger angles, indicating an increase in stability. </p> <p>The data collected and presented herein provide a unique, robust dataset to improve understanding of the effects of changing stagger angles on variable inlet guide vanes on multistage axial compressors. These data correspondingly provide a unique training set and validation method for predictive technology. </p>

Understanding distortion transfer and generation through fan and compressor blade rows is able to assist in blade design and performance prediction. Using full annulus unsteady RANS simulations, the effects of distortion as it passes through the rotor of a transonic fan at five radial locations (10%, 30%, 50%, 70%, and 90% span) are analyzed. The inlet distortion profile is a 90-degree sector with a 15% total pressure deficit. Fourier distortion descriptors are used in this study to quantitatively describe distortion transfer and generation. Results are presented and compared for three operating points (near-stall, design, and choke). These results are used to explain the relationship between inlet total pressure distortion, pressure-induced swirl, total pressure distortion transfer, total temperature distortion generation, and circumferential rotor work variation. It is shown that very large changes in pressure-induced swirl and distortion transfer and generation occur between near-stall and design, but only small changes are seen between design and choke. The greatest changes are shown to be near the tip. Local power variations are shown to correlate with total pressure distortion transfer and total temperature distortion generation.It can be difficult to predict the transfer of distortion through a fan or compressor because traditional experimental and computational methods are very expensive and time consuming. The Harmonic Balance approach is a promising alternative which uses Fourier techniques to represent fluid flow solutions and which can provide unsteady solutions much more quickly than traditional unsteady solvers. Relatively little work has been done to assess how much Fourier information is necessary to calculate a sufficiently accurate solution with the Harmonic Balance Solver. A study is performed to analyze the effects of varying the amount of modal content that is used in Harmonic Balance simulations. Inlet distortion profiles with varying magnitudes are used in order to analyze trends and provide insight into the distortion flow physics for various inlet conditions. The geometry is a single stage axial compressor that consists of an inlet guide vane followed by the NASA Stage 37 rotor. It is shown that simulations with greater magnitudes of distortion require more modal content in order to achieve sufficiently accurate results. Harmonic Balance simulations are shown to have significantly lower computational costs than simulations with a conventional unsteady solver.

No description available.