[pt] O presente trabalho investigou a queda de pressão em escoamento através de um espaço anular com rotação do cilindro interno. A motivação para o trabalho veio da aplicação desta configuração em diversas situações de interesse industrial, como reatores químicos catalíticos, filtros e nas operações de perfuração de poços produtores de petróleo e gás. O estudo realizado foi conduzido em uma seção de testes especialmente projetada e construída, formando um espaço anular com razão de raios de 0,65 e com um comprimento de 256 diâmetros hidráulicos, suficiente para garantir o desenvolvimento hidrodinâmico do escoamento nos regimes laminar e turbulento. O trabalho investigou a queda de pressão ao longo do espaço anular como função da vazão, dada pelo número de Reynolds, e da rotação do cilindro interno, caracterizada pelo número de Reynolds rotacional. A faixa de números de Reynolds investigada foi de 260 a 10000, enquanto o Reynolds rotacional variou de 60 a 1000. Dois fluidos de trabalho foram utilizados nos testes: água e uma mistura de água e glicerina. Os resultados para a queda de pressão foram apresentados na forma de fatores de atrito hidrodinâmicos. Testes preliminares para o caso do cilindro interno sem rotação foram realizados e comparados com resultados da literatura, com o objetivo de validar a seção de testes e o procedimento experimental. Os resultados apresentados mostraram boa concordância com valores disponíveis na literatura tanto para o caso de escoamento laminar , quanto para escoamento turbulento. Para os casos de baixos números de Reynolds, os resultados mostraram que a rotação do cilindro interno provocava um pico na razão entre o fator de atrito com rotação e sem rotação para um valor do número de Reynolds da ordem de 500. Aumentos da ordem de 15% foram verificados. / [en] The present work investigated the pressure drop generated by the flow through an annular configuration with rotation of the inner cylinder. The motivation for the work comes from the several industrial application of the configuration, such as chemical reactors, filters and in drilling operations for oil and gas wells. The experimental study was conducted in a specially designed test section forming an annular space with radius ratio of 0.65 and a length equivalent to 265 hydraulic diameters, what guaranteed the hydrodynamic development of the flow for the laminar and turbulent regimes. The study investigated the pressure drop along the annular space as a function of the flow rate, given by the Reynolds number, and of the rotation of the inner cylinder, given by the rotational Reynolds number. The range of Reynolds number investigated was from 260 to 10,000, while the rotational Reynolds number was varied from 60 to 1,000. Two fluids were employed in the testes; water and a mixture of water and glycerol. The pressure drop results were presented in the form of dimensionless friction factors. Preliminary tests for the case of no rotation of the inner cylinder were compared with results available in the literature, in order to validate the test section and the experimental procedure. The results displayed good agreement with the literature for both laminar and turbulent regimes. For the low Reynolds number test cases, the results obtained have shown that the inner cylinder rotation induces a peak in the distribution of the ratio of friction factor to the friction factor without rotation. The peak, of about 15%, is found for Reynolds numbers of the order of 500.

Axial compressors are used in a wide variety of aerodynamic applications and are one of the most important components in aero-engines. The operability of compressors is however limited at low-mass flow rates by fluid dynamic instabilities such as stall and surge. These instabilities can lead to engine failure and loss of engine power which can compromise the aircraft safety and reliability. Therefore, a better understanding of how stall occurs and the causes behind its inception is extremely important. In the vicinity of the stall line, the flow field is inherently unsteady due to the interactions between adjacent rows of blades, formation of separation cells, and the viscous effects including shock-boundary layer interaction. Accurate modeling of these phenomena requires a proper set of stable and accurate boundary conditions at the rotorstator interface that conserve mass, momentum and energy, while eliminating false reflections. As a part of this effort, an existing 3D Navier-Stokes analysis for modeling single stage compressors has been modified to model multi-stage axial compressors and turbines. Several rotor-stator interface boundary conditions have been implemented. These have been evaluated for the first stage (a stator and a rotor) of the two stage fuel turbine on the space shuttle main engine (SSME). Their effectiveness in conserving global properties such as mass, momentum, and energy across the interface, while yielding good performance predictions has been evaluated. While all the methods gave satisfactory results, a characteristic based approach and an unsteady sliding mesh approach are found to work best. Accurate modeling of the formation of stall cells requires the use of advanced turbulence models. As a part of this effort, a new advanced turbulence model called Hybrid RANS/KES (HRKES) has been developed and implemented. This model solves Menter's k--SST model near walls and switches to a Kinetic Eddy Simulation (KES) model away from walls. The KES model solves directly for local turbulent kinetic energy and local turbulent length scales, alleviating the grid spacing dependency of the length scales found in other Detached Eddy Simulation (DES) and Hybrid RANS/LES (HRLES) models. Within the HRKES model, combinations of two different blending functions have been evaluated for blending the near wall model to the KES model. The use of realizability constraints to bound the KES model parameters has also been studied for several internal and external flows. The current methodology is used in the prediction of the performance map for the NASA Stage 35 compressor configuration as a representative of a modern compressor stage. The present approach is found to satisfactory predict the onset of stall. It is found that the rotor blade tip leakage vortex and its interaction with the shock wave is mainly the reason behind the stall inception in this compressor stage.

Thesis (MEng) -- Stellenbosch University, 2014. / ENGLISH ABSTRACT: The use of air-cooled steam condensers (ACSCs) is the preferred cooling method in the chemical and power industry due to stringent environmental and water use regulations. The performance of ACSCs is however highly dependent on the influence of windy conditions. Research has shown that the presence of wind reduces the performance of ACSCs. It has been found that cross-winds (wind perpendicular to the longest side of the ACSC) cause distorted inlet flow conditions, particularly at the upstream peripheral fans near the symmetry plane of the ACSC. These fans are subjected to what is referred to as '2-D' wind conditions, which are characterised by flow separation on the upstream edge of the fan inlets. Experimental investigations into inlet flow distortion have simulated these conditions by varying the fan platform height. Low platform heights resulted in higher levels of inlet flow distortion, as also found to exist with high cross-wind speeds. This investigation determines the performance of various fan configurations (representative of configurations used in the South- African power industry) subjected to distorted inlet flow conditions through experimental and numerical investigations. The similarity between platform height and cross-wind effects is also investigated and a correlation between system volumetric effectiveness, platform height and cross-wind velocity is found. / AFRIKAANSE OPSOMMING: Die gebruik van lugverkoelde stoom kondensors (LVSK's) word verkies as 'n verkoelingsmetode in die chemiese- en kragvoorsieningsindustrie as gevolg van streng omgewings- en waterverbruiksregulasies. Die werkverrigting van LVSK's word egter grootliks beïnvloed deur die teenwoordigheid van wind. Navorsing het gewys dat die teenwoordigheid van wind die werkverrigting van LVSK's verminder. Daar was gevind dat kruiswinde (wind loodreg tot die langste sy van die LVSK) versteurde inlaat vloeitoestande veroorsaak, veral by waaiers wat aan die stroomop kant van die LVSK naby die simmetrievlak geleë is. Hierdie waaiers word blootgestel aan na wat verwys word as '2-D' windtoestande wat gekenmerk word deur vloeiwegbreking wat plaasvind by die stroomop rand van die waaierinlate. Eksperimentele ondersoeke van inlaat vloeiversteurings het hierdie toestande gesimuleer deur die waaier platformhoogte te verstel. Lae platform hoogtes het gelei tot hoër vlakke van inlaat vloeiversteuring, soortgelyk aan wat gevind word met hoë kruiswindsnelhede. Hierdie ondersoek gebruik numeriese en eksperimentele metodes om die werkverrigting van verskeie waaierkon gurasies (verteenwoordigend van kon- gurasies wat gebruik word in die Suid-Afrikaanse kragvoorsieningsindustrie) wat blootgestel word aan versteurde inlaat vloeitoestande te bepaal. Die ooreenkoms tussen platformhoogte en kruiswind e ekte word ook ondersoek en 'n korrelasie tussen die sisteem volumetriese e ektiwiteit, platformhoogte en kruiswindsnelheid word bepaal.

In this study, a variable pitch axial flow fan is designed and analysed for Ankara Wind Tunnel (AWT). In order to determine the loss caharacteristics of AWT, an algorithm is developed and the results are validated. Also some pressure and velocity measurements are made at the fan section to find the losses experimentally. After completion of the fan design, analyses are made at different volumetric flowrates and blade angles including the design point and the performance characteristics of the fan are obtained and thereafter the operating range of the tunnel is deterimened.

Nous avons abordé dans ce travail deux aspects particuliers de la mécanique des fluides appliquées à la conception des matériels de lutte contre l’incendie. Le premier concerne la ventilation lors du traitement des compartiments. Nous avons montré qu’une grille alvéolaire, placée devant l’hélice du ventilateur, nous permet de façonner le jet et de lui donner une forme ovalisée. Cette forme est plus adéquate à l’entrant du compartiment et permet un gain important de la performance de ces ventilateurs. Le deuxième aspect de ce travail a été de concevoir un système de dosage d’émulseur dans un réseau d’eau sous pression. Nous avons pour cela défini un doseur de type venturi, équipé d’une ogive conique au niveau du col. Cette ogive, dont la position est définie par le rapport entre la pression d’entrée et la pression de sortie. Nous avons montré, à partir du théorème de Bernoulli, que ce système permet de maintenir une aspiration au niveau du col, quelle que soit la pression ou le débit le traversant. / In this work we have analysed two topics of fluid mechanics, applied to the design of fire fighting equipment. The first one is the performance of ventilation during the movement of air in a compartment that contains a fire. We have shown that specific blade angle designed within the gril and placed in front of the fan propeller, allows us to manipulate the jet of air giving it an oval shape. This shape is more efficient and allows a significant gain in the air movement performance within the compartment for these fans. The second aspect of this work was to define an emulsifier dosing system in a pressurized water system. We define a venturi dosing system with a movable cone piece. The position of this conical piece is Controlled by the pressure ratio between the inlet and the outlet. Based on Bernoulli's theorem, we have demontrated that this system maintains a level of suction at the Inlet regardless of the pressure or flow passing through it.

<p>      Rotating detonation combustion has been investigated since the 1960s and has gained much attention in the past decade due to its promise of pressure gain. In theory, the pressure gain can provide higher power output at inlet total temperatures similar to those of Brayton cycle engines, leading to increased efficiency and decreased engine size. However, complexities presented by detonative combustion have prevented it from becoming widely adopted, especially for turbomachinery applications. A rotating detonation combustor with a transonic or supersonic exhaust imposes rapid fluctuations in pressure, temperature, and flow angle at the inlet of the turbine. To account for these fluctuations, ad hoc turbine designs have been proposed over the last few years, including supersonic bladed and bladeless variants. Computational fluid dynamics simulations have shown that it is possible to extract a meaningful amount of work from these turbines, but dedicated experimental test rigs are needed to validate these designs at relevant conditions in long-duration tests.</p> <p>     Toward this goal, this thesis focuses on three research elements. The first element is the design of a cooled rotating detonation combustor with a downstream turbine that can operate for long durations. The cooled combustor is accomplished in a two-part procedure: (1) repurposing Purdue University’s Turbine-integrated High-pressure Optical Rotating detonation engine (THOR) and (2) designing a lightweight, gaseous film-cooled combustor shroud with ample configurations for pressure, temperature, and optical measurements.</p> <p>     The second element is the design of three supersonic turbines for use in RDEs: an axial-flow bladed turbine, an axial-flow bladeless turbine, and an axial-inflow/radial-outflow bladed turbine. Each turbine is designed for cold flow testing, and provisions for mounting the axial-flow bladed turbine downstream of the cooled combustor are proposed. Supplemental turbine hardware is also designed to provide precise and repeatable conditions for the turbine tests.</p> <p>     The third element is the construction of an energy absorption dynamometer to measure the power output of the different supersonic turbines. Four types of dynamometers are explored, including hydraulic brakes, electromagnetic brakes, electric generator brakes, and airbrakes. Although the literature declares the electromagnetic brake to be more accurate, the most cost-effective solution is to utilize the compressor side of a donated turbocharger. Combining all research elements yields a new test rig for this new class of supersonic turbines.</p>

No description available.

A three dimensional computational model of a full scale axial flow tidal turbine has been used to investigate the effects of a range of realistic environmental conditions on turbine performance. The model, which is based on the Reynolds averaged Navier-Stokes equations, has been developed using the commercial flow solver ANSYS Fluent. A 1:30 scale tidal turbine is simulated in an open channel for comparison to existing experimental data. The rotor blades are directly resolved using a body-fitted, unstructured computational grid. Rotor motion is enabled through a sliding mesh interface between the rotor and the channel boundaries. Reasonably good agreement in thrust and power is observed. The computed performance curves are offset from the measured performance curves by a small increment in rotor speed. Subsequently, a full scale axial flow turbine is modelled in a variety of conditions representative of tidal channel flows. A parametric study is carried out to investigate the effects of flow shear, confinement and alignment on turbine performance, structural loading, and wake recovery. Mean power and thrust are found to be higher in sheared flow, relative to uniform flow of equivalent volumetric flow rate. Large fluctuations in blade thrust and torque occur in sheared flow as the blade passes through the high velocity freestream flow in the upper portion of the profile and the lower velocity flow near the channel bed. A stronger shear layer is formed around the upper portion of the wake in sheared flow, leading to enhanced wake mixing. Mean power and thrust are reduced when the turbine is simulated at a lower position in a sheared velocity profile. However, fluctuations in blade loading are increased due to the higher velocity gradient. The opposite effects are observed when the turbine operates at greater heights in sheared flow. Flow misalignment has a negative impact on mean rotor thrust and power, as well as on unsteady blade loading. Although the range of unsteady loading is not increased significantly, additional perturbations are introduced due to interactions between the blade and the nacelle. A deforming surface is introduced using the volume-of-fluid method. Linear wave theory is combined with the existing free surface model to develop an unsteady inflow boundary condition prescribing combined sheared flow and free surface waves. The relative effects of the sheared profile and wave-induced velocities on turbine loading are identified through frequency analysis. Rotor and blade load fluctuations are found to increase with wave height and wave length. In a separate study, the performance of bi-directional ducted tidal turbines is investigated through a parametric study of a range of duct profiles. A two dimensional axi-symmetric computational model is developed to compare the ducted geometries with an unducted device under consistent blockage conditions. The best-performing ducted device achieves a peak power coefficient of approximately 45% of that of the unducted device. Comparisons of streamtube area, velocity and pressure for the flow through the ducted device shows that the duct limits the pressure drop across the rotor and the mass flow through the rotor, resulting in lower device power.

Le bruit tonal d’interaction rotor-stator, généré par l’impact des sillages issus des pales d’un rotorsur la grille d’aubes d’un stator redresseur, contribue de manière déterminante au bruit d’origineaérodynamique des turbomachines axiales carénées, qui équipent une large part des systèmes de propulsionaéronautique et de conditionnement d’air. La prédiction du bruit par l’utilisation de simulationsnumériques demeure onéreuse, notamment dans les premières phases de conception lorsque de nombreusesconfigurations doivent être testées. Dans cette optique, l’approche analytique choisie dans cettethèse apporte une alternative tout à fait appropriée. Les modèles analytiques basés sur une fonctionde réponse aéroacoustique de profil isolé ne permettent pas de reproduire l’effet de grille engendrépar le nombre important d’aubes de stator. Inversement, de fortes approximations sont nécessairespour décliner les fonctions de réponse de grilles d’aubes existantes dans des configurations tridimensionnelles.Le formalisme proposé, basé sur la méthode de raccordement modal, permet d’introduiresimplement l’effet de grille dans une géométrie annulaire d’étage rotor-stator. Un modèle de réponse degrille rectilinéaire bidimensionnel est tout d’abord présenté pour la transmission d’ondes acoustiques àtravers le stator ainsi que pour la génération de bruit par l’impact de rafales hydrodynamiques. Dansce cadre, une analyse linéaire et non visqueuse est considérée, pour laquelle les modes acoustique ettourbillonnaire d’un gaz sont couplés par le biais des frontières rigides. Les perturbations de vitessesliées aux sillages sont modélisées comme des rafales convectées. Leur impact sur la grille de statorgénère des ondes acoustiques se propageant en amont, en aval ainsi que dans les espaces inter-aubesdu stator, vu comme un réseau périodique de guides d’ondes. Les sections de bords d’attaque et defuite des aubes sont considérées comme des interfaces sur lesquelles la continuité des fluctuations depression, de vitesse axiale et de vorticité est vérifiée. Un système d’équations est ainsi obtenu, puisrésolu par des projections sur les bases modales du conduit et des inversions matricielles. Le champacoustique rayonné est ainsi déterminé uniformément dans tout le domaine. Les résultats issus de cesmodélisations sont comparés à ceux des fonctions de réponse de grilles d’aubes rectilinéaires issues dela littérature, montrant un très bon accord avec les modèles basés sur la technique de Wiener-Hopf. Leformalisme est par la suite étendu aux grilles annulaires par l’ajout de fonctions de Bessel comme fonctionsde forme radiale exprimant les effets tridimensionnels. Finalement, une procédure est présentéepour rendre compte de l’hétérogénéité des aubes de stator, caractéristique des nouvelles architecturesde turbomachines. Cette méthodologie est basée sur l’emploi conjoint du principe du dipôle de bordd’attaque et de la fonction de réponse aéracoustique de la grille de stator à l’aide de la technique deraccordement modal. Le principe de dipôle de bord identifie le chargement instationnaire des aubesinduit par l’impact de rafales hydrodynamiques, calculé par le formalisme d’Amiet, avec la trace duchamp de pression acoustique produit par un dipôle placé au voisinage du bord de l’aube. Les prédictionsissues de ce modèle, appliqué dans un cadre bidimensionnel, sont ensuite comparées à des mesuresobtenues pendant la campagne d’essais du projet SEMAFOR. / The rotor-stator wake-interaction tonal noise, generated by the impingement of rotor wakes onoutlet guide vanes, plays a crucial role in the aerodynamic noise of axial-flow ducted fan stages. Thelatter are widely used in most aeronautic propulsion and air-conditioning systems. The noise predictionby means of numerical simulations remains expensive, especially at the preliminary design stage whennumerous configurations must be tested. In this respect, the analytical approach chosen in this thesisprovides a well suited alternative. The analytical modeling based on an isolated-airfoil response functioncan not reproduce the cascade effect introduced by the large number of stator vanes. Conversely, drasticapproximations are required to extend the current cascade response functions to three-dimensionalconfigurations. The proposed modeling based on the mode-matching technique simply introduces thecascade effect in an annular rotor-stator stage. A rectilinear cascade response function is firstly presentedto account for the acoustic transmission through the stator along with the wake-interaction noise.In this context, a linearized and non-viscous analysis is carried out, in which the acoustic and vorticalmodes of a gas are coupled at rigid physical boundaries. The velocity perturbations issued from thewakes are written as a sum of convected gusts. Their impingement on the cascade of vanes generatesacoustic waves propagating upstream, downstream of the cascade, as well as inside the inter-vane channelsof the stator, seen as a periodic array of bifurcated waveguides. The duct cross sections at theleading-edge and the trailing-edge of the vanes are seen as interfaces on which the continuity of thefluctuating pressure, axial velocity and vorticity is fulfilled. A system of linear equations is obtained,then solved by means of modal projections and matrix inversions. The acoustic field is then uniformlycalculated in the whole domain. Comparisons with rectilinear cascade response functions show a verygood agreement with predictions based on the Wiener-Hopf technique. The configuration of an annularcascade is addressed by introducing the Bessel functions as radial shape functions, expressing threedimensionaleffects. Finally, a procedure is presented to account for the heterogeneity of the statorvanes, typical of modern fan architectures. This approach is based on the combinaison of the leadingedgedipole principle and the cascade response function derived from the mode-matching technique.The edge-dipole principle identifies Amiet’s solution for the unsteady loading and the radiation of adipole approached very close to the edge of a half plane. The predictions provided by this modeling,applied in a two-dimensional configuration, are finaly compared to measurements performed in the testcampaign of the SEMAFOR project.

La chromatographie membranaire est une alternative à la chromatographie classique sur résine basée sur le transport convectif des solutés à travers une membrane microporeuse plutôt que par le transport diffusif des solutés dans les particules de résines. Cette technique présente les avantages de diminuer les phénomènes de diffusion, de réduire les temps de séjour et les pertes de charge, et de permettre la purification rapide de quantités importantes de molécules. La chromatographie membranaire connaît un fort succès commercial. Une gamme importante de membranes chromatographiques mettant en jeu différents mécanismes de rétention (échange d’ions, affinité, etc.) et différentes géométries (feuille, spirale, etc.) est actuellement commercialisée. Malgré ce succès, différents aspects relatifs à la chromatographie membranaire restent mal connus. Cette thèse de doctorat se propose de répondre à certaines questions relatives à cette technique / Membrane chromatography (MC) is an alternative to traditional resin packed columns chromatography. The solute mass transport in the membrane occurs in convective through-pores rather than in stagnant fluid inside the pores of the resins particles, which is limited by the slow diffusive transport. MC offers the main advantage of reducing diffusion phenomena, shorter residence time and lowered pressures drops, and thus, facilitates rapid purification of large quantities of molecules. A wide range of chromatographic membranes involving different molecules retention mechanisms (ion exchange, affinity, etc...) is now commercialized. Despite their success, the influence of the geometry of the membrane chromatography devices remains relatively unexplored from a theoretical point of view. This doctoral thesis is aimed to clarify some ambiguous points related to this technique