The production from an oil reservoir is a mixture of liquids (oil and water) and gas, and is often maintained by using a pump placed in the well to ensure a continuous flow to the surface. Electrical Submersible Pumps consist of stacked centrifugal pump stages, each comprising a bladed impeller (rotating part) and diffuser (stationary part). In multiphase conditions, the gas tends to accumulate in the impeller, severely reducing the pressure produced by the pump. Radial-flow pumps operate in a plane perpendicular to their rotation axis, while mixed-flow pumps are characterised by a lower meridional angle (generally 40 to 80 degrees), and are generally better at handling gas-liquid mixtures. We first describe the impact of gas on the whole pumping system, from the reservoir to the storage facility, and give context to the subject. The available literature shows that the size of the gas bubbles present in the fluid is critical to the pump performance. A transparent, full-scale pump was built in order to explore the flow features in single and multiphase flows. Laser Doppler Velocimetry and high speed imaging in single phase flow showed a high turbulence level in the wake of the impeller blades, and recirculation cells at low flow rates. In gas-liquid conditions, we demonstrated that the bubble size varies within a pump stage, as break-up occurs at the impeller tip, and coalescence is dominant in the diffuser, especially because of recirculation. The first impeller acted as a mixer, and at moderate to high gas fractions (10 to 30%), the flow patterns at the stage level alternated between bubbly and radially separated flows. Finally, a dispersed-gas model was developed to predict the pressure rise in a mixed-flow pump impeller under gas-liquid conditions. This model based on the forces acting on a single spherical gas bubble, was implemented with a simplified, parametric representation of the flow field in a mixed-flow impeller. In the meridional direction, the Coriolis force opposes the centrifugal force and the adverse pressure gradient. Both forces tend to retain the gas bubble within the impeller. The relative magnitude of the drag force strongly depends on the maximal bubble diameter, which was determined as a function of the flow conditions and used to calculate the gas velocity through the impeller. This method resulted in a better agreement with the experimental data than a one-dimensional two-fluid model where the gas phase follows the same path as the liquid. We used the dispersed-gas model to give quantitative evidence that low blade and meridional angles reduce the gas accumulation and the associated performance degradation.

[pt] O presente trabalho é um estudo experimental das características de um escoamento de ar em forma de jato espiralado, incidindo ortogonalmente sobre uma placa. Os objetivos do estudo são: avaliar a influência da presença de uma componente circunferencial de velocidade na distribuição dos coeficientes locais de troca de calor, obter campos de velocidade instantâneos no plano axissimétrico assim como informações sobre as características da turbulência no escoamento. Durante os experimentos se investigou a influência da distância jato/placa e da intensidade do escoamento espiralado (número de Swirl). Como etapa preliminar, foi conduzido um experimento de jato livre, para validação das técnicas de medição de velocidade utilizadas. Os resultados foram comparados com os da literartura e uma boa concordância foi obtida. A distribuição espacial dos coeficientes de troca de calor foi avaliada impondo-se um fluxo de calor constante na placa e medindo a distribuição radial de temperatura através de diversos termopares. Coeficientes locais puderam então ser estimados. Os campos de velocidades radial e axial instantâneos foram adquiridos experimentalmente através da utilização da técnica de Particle Image Velocimetry (PIV) e perfis de velocidade tangencial (média e flutuações) foram obtidos a partir da técnica Laser Doppler Velocimetry (LDV). Os resultados mostraram que os padrões de escoamento mudam significativamente quando a componente circunferencial de velocidade é introduzida. Para o valor mais alto do Número de Swirl foram verificadas fortes reversões do escoamento na região de estagnação. / [en] The present work is an experimental study of the characteristics of a swirling impinging air jet. The goals of the study are: to evaluate the influence of the presence of a circumferential velocity component in the distribution of the local heat transfer coefficients, to obtain instantaneous velocity fields in the axisymmetric plane, as well as information about the turbulence characteristics in the flow. During the experiments, the influence of the impingement distance and swirl intensity were investigated. As a preliminary validation of the velocity measurement tecniques, an experimental investigation of an axisymmetric free jet was conducted. The results were compared with literature showing good agreement. The spatial distribution of heat transfer coefficients was evaluated by imposing a constant heat flux condition to the plate and measuring temperature of several points along the radial distance of the plate with thermocouples. Local coefficients could then be estimated. Instantaneous axial and radial velocity fields were obtained with Particle Image Velocimetry (PIV) and tangential velocity profiles (mean and fluctuations) obtained by using Laser Doppler Velocimetry (LDV). The results showed that the flow patterns change significantly when the tangential component is added. For the highest value of Swirl number, strong recirculation zones were observed in the stagnation region.

L’effet du vol d’avancement sur le bruit de choc de jets supersoniques sous-détendus est étudié de manière expérimentale. La structure de tels jets est d’abord explorée, avec et sans vol simulé. L’analyse employée allie des visualisations strioscopiques à des mesures quantitatives de pression statique et de vitesse, par vélocimétrie laser Doppler et vélocimétrie par images de particules. L’accent est mis sur l’étude de l’écoulement moyen et des propriétés de la turbulence dans la couche de mélange. L’effet du vol sur la composante tonale du bruit de choc, le screech, est ensuite examiné. A l’aide d’une antenne azimutale de microphones placée dans le champ proche acoustique, une analyse fine des modes du screech est notamment proposée. Par ailleurs, plusieurs effets de cette composante de bruit sur la dynamique du jet sont mis en évidence, en particulier l’oscillation des chocs ; on montre que cette oscillation est intimement liée au mode du screech. De manière à étudier spécifiquement la composante large bande du bruit de choc, diverses techniques de suppression du screech sont ensuite explorées.L’utilisation d’une tuyère crénelée s’est révélée satisfaisante pour l’éliminer de manière non-intrusive et a permis de déduire son influence sur le bruit de choc large bande. Enfin, l’effet du vol sur cette dernière composante est déterminé par l’étude de l’évolution de sa fréquence centrale, de son amplitude et de sa forme spectrale en situation de vol simulé. Une explication des tendances observées est alors proposée à la lumière des résultats aérodynamiques obtenus. / The flight effects on the shock-associated noise components of underexpanded supersonic jets are experimentally studied. To begin with, the jet structure is investigated, with and without simulated flight. To that end, Schlieren visualizations are combined with quantitative measurements of static pressure and velocity, by laser Doppler velocimetry and particle image velocimetry. The investigation focuses on the mean flow and on the properties of the mixing layer turbulence. Then, the effects of flight on the tonal component of shock-associated noise, the so-called screech, are studied. By means of a near field, azimuthal microphone antenna, a detailed analysis of its modal behaviour is proposed. Furthermore, several effects of screech on the jet dynamics are highlighted, like the shock oscillations. It is shown that these oscillations are closely connected to the screech mode. In order to study specifically the broadband component of shock-associated noise, several screech suppression techniques are considered. It is found that a notched nozzle is successful in non-intrusively suppressing it. This device is then used to deduce the screech influence on the broadband shock-associated noise.Finally, some effects of flight on the latter component are pinpointed through the study of the evolutionof its amplitude, peak frequency and spectral shape under flight conditions. The observed tendencies are explained in light of the aerodynamic results obtained.

De nos jours, l’énergie délivrée par la combustion dépasse 80% de l‟énergie totale dans le monde, et ce pourcentage restera probablement élevé le long des 100 prochaines années. La plupart des systèmes réactifs qui génèrent la combustion turbulente sont utilisés dans la fabrication, le transport et l‟industrie pour la génération des puissances. Comme résultat, l‟émission des polluants est parmi les problèmes majeurs qui sont devenus des facteurs critiques dans notre société. Dans ce cadre, une étude détaillée des systèmes réactifs est alors nécessaire pour la conception de systèmes de haute performance qui s‟adaptent aux technologies modernes. L'optimisation des performances de ces systèmes énergétiques permet d‟une part d‟économiser l'énergie et d‟autre part de réduire la pollution. Les jets turbulents sont impliqués dans l'efficacité de ces divers systèmes. Dans le cas isotherme, la complexité des écoulements turbulents résulte principalement de la coexistence des structures de tailles très différentes et de l‟interaction non linéaire entre ces structures. Les plus grandes structures dépendent fortement de la géométrie du domaine considéré, elles sont donc anisotropes. De plus, elles ont une grande durée de vie et elles sont responsables du transport de la quasi-totalité de l'énergie. Les plus petites structures, quant à elles, ont souvent un caractère beaucoup plus "universel" (dû à leur comportement relativement isotrope) et sont à l'origine du processus de dissipation visqueuse. Prédire numériquement la dispersion et le mélange d‟un scalaire non réactif dans un écoulement turbulent est considéré comme un problème primordial et reste toujours actuel. Plusieurs recherches sont attachés à ce sujet afin d‟approfondir de plus à la connaissance de différents phénomènes pour pouvoir les mieux prédire. La prédiction numérique du mélange turbulent existant dans plusieurs applications industrielles et environnementales, a un important intérêt en génie chimique. Il est nécessaire donc de bien comprendre la majorité de propriétés du mélange et de l‟écoulement. En combustion, la complication du comportement des jets résulte de l‟interaction entre le dégagement de la chaleur, les processus de mélange, l'entraînement et la recirculation des gaz. Pour bien comprendre la complexité de ce phénomène, il est nécessaire de connaître parfaitement l'évolution dynamique et scalaire des jets turbulents isothermes en présence d'importantes différences de densité, comme elles peuvent lors de la combustion. Cette optimisation passe par la compréhension de l'effet de la variation des conditions d'entrée sur les processus de mélange dans le cas non réactif et sur la stabilité et la nature de la flamme dans le cas réactif. Ainsi, des études théoriques, expérimentales et numériques, doivent être menées en parallèle pour mieux identifier les effets d'une telle intervention. Bien des questions demeurent ouvertes dans le but de mieux caractériser les différents écoulements turbulents réactifs. Les objectifs des études menées dans ce domaine sont la réduction des émissions de polluants et l‟amélioration du rendement de combustion. Une compréhension du mélange et leur interaction avec les différents processus chimiques traduit donc un enjeu majeur. Elle est considéré alors comme un facteur déterminant la qualité des variétés des procèdes. Ce travail de thèse se base sur les jets coaxiaux qui constituent un cas particulier de jet axisymétrique. Ils sont communément rencontrés dans des différents brûleurs industriels qui assurent le contact entre le comburant et le carburant sous une forme de jets coaxiaux. Cette technique est le siège d‟une amélioration du mélange et de la stabilité des flammes. / Résumé non fourni

This thesis deals with turbulent flows in 90 degree curved pipes of circular cross-section. The flow cases investigated experimentally are turbulent flow with and without an additional motion, swirling or pulsating, superposed on the primary flow. The aim is to investigate these complex flows in detail both in terms of statistical quantities as well as vortical structures that are apparent when curvature is present. Such a flow field can contain strong secondary flow in a plane normal to the main flow direction as well as reverse flow. The motivation of the study has mainly been the presence of highly pulsating turbulent flow through complex geometries, including sharp bends, in the gas exchange system of Internal Combustion Engines (ICE). On the other hand, the industrial relevance and importance of the other type of flows were not underestimated. The geometry used was curved pipes of different curvature ratios, mounted at the exit of straight pipe sections which constituted the inflow conditions. Two experimental set ups have been used. In the first one, fully developed turbulent flow with a well defined inflow condition was fed into the pipe bend. A swirling motion could be applied in order to study the interaction between the swirl and the secondary flow induced by the bend itself. In the second set up a highly pulsating flow (up to 40 Hz) was achieved by rotating a valve located at a short distance upstream from the measurement site. In this case engine-like conditions were examined, where the turbulent flow into the bend is non-developed and the pipe bend is sharp. In addition to flow measurements, the effect of non-ideal flow conditions on the performance of a turbocharger was investigated. Three different experimental techniques were employed to study the flow field. Time-resolved stereoscopic particle image velocimetry was used in order to visualize but also quantify the secondary motions at different downstream stations from the pipe bend while combined hot-/cold-wire anemometry was used for statistical analysis. Laser Doppler velocimetry was mainly employed for validation of the aforementioned experimental methods. The three-dimensional flow field depicting varying vortical patterns has been captured under turbulent steady, swirling and pulsating flow conditions, for parameter values for which experimental evidence has been missing in literature. / QC 20120425

<p>  </p> <p>As aviation fuel costs and consumption have continued to rise over recent decades, gas turbine engine manufacturers have sought methods to reduce fuel burn. Manufacturers plan to achieve this by reducing the specific fuel consumption of the machine by increasing the bypass ratio through a reduction of the diameter of the engine core. This presents an opportunity for implementing a centrifugal compressor as the final stage of the high-pressure compressor. The vaned diffuser in a centrifugal compressor stage maintains an integral role in determining the extents of the operating range as well as conditioning the flow for the downstream combustor. Thus, it is critical to understand the aerodynamics and performance of the vaned diffuser across the entire compressor operating range.</p> <p>This investigation focused on seven compressor operating points at the stage’s design corrected speed, which ranged from choked flow to the minimum mass flow rate before rotating stall. Steady-state and unsteady performance data were acquired to study the aerodynamics at each operating point as well as the steady-state performance of the vaned diffuser. Laser Doppler velocimetry, high-frequency pressure transducers, and additive manufacturing techniques were all implemented to acquire data in the research compressor.</p> <p>Unsteady velocity measurements were acquired in the vaneless space and were used to quantify the change in diffuser inlet incidence as the stage mass flow rate changes. The impeller exit jet and wake were compared at each operating point to understand the effect of these flow structures on the spanwise incidence profile. Steady-state performance metrics for the vaned diffuser were compared with the change in incidence to assess the effect of incidence on performance. Maximum static pressure recovery and minimum total pressure loss occurred at the maximum incidence operating point. </p> <p>The chordwise static pressure distribution is critical for health monitoring of the polymer, additive manufactured diffuser vanes. Steady-state and unsteady pressure measurements were acquired along the diffuser vane surface to assess the change in the aerodynamic lift force across the compressor operating range as well as the static pressure differential across the vane leading edge. The maximum unsteady lift on the diffuser vanes was up to 34% greater than the steady-state lift force. Unsteady static pressure differentials across the diffuser vane leading edge were similar to the steady-state values, but they were marginally greater across the entire examined operating range. These unsteady pressure measurements were acquired with high-frequency response pressure transducers installed along the diffuser vane surfaces. These transducers were also used to study the rotating stall and surge behavior of the investigated centrifugal compressor stage. This centrifugal compressor stage exhibits a spike-type rotating stall pattern at the onset of stage instability, which rapidly evolves into full flow reversal with several surge cycles. During these surge cycles, the diffuser vane leading edges are subject to a 20 psid static pressure differential. </p> <p>A computational model was used to predict the compressor flow at three different operating points. This model utilized the BSL-EARSM turbulence model, and it included surface roughness and an experimentally measured shroud thermal profile. The model accurately predicted the diffuser inlet flow angles near the shroud, but it predicted more radial flow near midspan. The diffuser vane leading edge static pressure differential was predicted within 1 psid at higher aerodynamic loading conditions. The differences between the computationally predicted and experimentally measured flow are attributed to difficulties associated with modelling the rate of mixing within the flow.</p>

This dissertation presents results from a thorough study of the tip-gap turbulent flow structure in a low-speed linear compressor cascade wind tunnel at Virginia Tech that includes a moving belt system to simulate the relative motion between the tip and the casing. The endwall pressure measurements and the surface oil flow visualizations were made on a stationary endwall to obtain the flow features and to determine the measurement profiles of interest. A custom-made miniature 3-orthogonal-velocity-component fiber-optic laser-Doppler velocimetry (LDV) system was used to measure all three components of velocity within a 50 mm spherical measurement volume within the gap between the endwall and the blade tip, mainly for the stationary wall with 1.65% and 3.30% tip gaps as well as some initial experiments for the moving wall. Since all of the vorticity in a flow originates from the surfaces under the action of strong pressure gradient, it was very important to measure the nearest-wall flow on the endwall and around the blade tip. The surface skin friction velocity was measured by using viscous sublayer velocity profiles, which verified the presence of an intense lateral shear layer that was observed from surface oil flow visualizations. All second- and third-order turbulence quantities were measured to provide detailed data for any parallel CFD efforts. The most complete data sets were acquired for 1.65% and 3.30% tip gap/chord ratios in a low-speed linear compressor cascade. This study found that tip gap flows are complex pressure-driven, unsteady three-dimensional turbulent flows. The crossflow velocity normal to the blade chord is nearly uniform in the mid tip-gap and changes substantially from the pressure to suction side. The crossflow velocity relies on the local tip pressure loading that is different from the mid-span pressure loading because of tip leakage vortex influence. The tip gap flow is highly skewed three-dimensional flow throughout the full gap. Normalized circulation within the tip gap is independent of the gap size. The tip gap flow interacts with the primary flow, separates from the endwall, and rolls up on the suction side to form the tip leakage vortex. The tip leakage vortex is unsteady from the observation of the TKE transport vector and oil flow visualizations. The reattachment of tip separation vortex on the pressure side strongly depends on the blade thickness-to-gap height ratio after the origin of tip leakage vortex but is weakly related to it before the origin of tip leakage vortex for a moderate tip gap. Other than the nearest endwall and blade tip regions, the TKE does not vary much in tip gap. The tip leakage vortex produces high turbulence intensities. The tip gap flow correlations of streamwise and wall normal velocity fluctuations decrease significantly from the leading edge to the trailing edge of the blade due to flow skewing. The tip gap flow is a strongly anisotropic turbulent flow. Rapid distortion ideas can not apply to it. A turbulence model based on stress transport equations and experimental data is necessary to reflect the tip gap flow physics. For the moving endwall, relative motion skews the inner region flow and is decorrelated with the outer layer flow. Hence, the TKE and correlations of streamwise and wall normal velocity fluctuations decrease. / Ph. D.

Modeling the effects of surface roughness is an area of concern in many practical engineering applications. Many current roughness models to this point have involved the use of empirical 'constants' and equivalent sand grain roughness. These underdeveloped concepts have little direct relationship to realistic roughness and cannot predict accurately and consistently the flow characteristics for different roughness shapes. In order to aid in the development of turbulence models, the present research is centered around the experimental investigation of seven various shaped single roughness elements and their effects on turbulence quantities in a two-dimensional turbulent boundary layer. The elements under scrutiny are as follows: cone, cone with spatial variations equal to the smallest sublayer structure length scale, cone with spatial variations equal to 2.5 times the smallest sublayer structure length scale, Gaussian-shaped element, hemisphere, cube aligned perpendicular to the flow (cube at 90&#176;), and a cube rotated 45&#176; relative to the flow. The roughness element heights, k+, non-dimensionalized by the friction velocity (U_tau) of the approaching turbulent boundary layer, are 145, 145, 145, 145, 80, 98, and 98 respectively. Analysis of a three-dimensional fetch of the same Gaussian-shaped elements described previously was also undertaken. In order to analyze the complex flow fields, detailed measurements were obtained using a fine-measurement-volume (50 micron diameter) three-velocity component laser-Doppler velocimetry (LDV) system. The data reveals the formation of a horseshoe vortex in front of the element, which induces the downwash of higher momentum fluid toward the wall. This 'sweep' motion not only creates high Reynolds stresses (v^2, w^2, -uv) downstream of the element, but also leads to higher skin-friction drag. Triple products were also found to be very significant near the height of the element. These parameters are important in regards to the contribution of the production and diffusion of the turbulent kinetic energy in the flow. The 'peakiness' of the roughness element was found to have a direct correlation to the production of circulation, whereas the spatial smoothing does not have an immense effect on this parameter. The peaked elements were found to have a similar trend in the decay of circulation in the streamwise direction. These elements tend to show a decay proportional to (x/d)^-1.12, whereas the cube elements and the hemisphere do not have a common trend. A model equation is proposed for a drag correlation common to all roughness elements. This equation takes into account the viscous drag and pressure drag terms in the calculation of the actual drag due to the roughness elements presence in the boundary layer. The size, shape, frontal and wetted surface areas of the roughness elements are related to one another via this model equation. Flow drawings related to each element are presented which gives rise to a deeper understanding of the physics of the flow associated with each roughness element. / Master of Science

The work presented in this thesis was on nominally two-dimensional turbulent boundary layers at zero pressure gradient subjected to high free-stream turbulent intensities of up to 7.9% in preparations for high free-stream turbulence studies on three-dimensional boundary layers, which will be done in the future in the Aerospace and Ocean Engineering Boundary Layer Wind Tunnel at Virginia Tech. The two-dimensional turbulent flow that will impinge three-dimensional bodies needed to be characterized, before the three-dimensional studies can be made. An active turbulence generator designed to create high free-stream turbulence intensities in the wind tunnel was tested and modified in order to obtain the lowest possible mean flow non-uniformities. A seven-hole pressure probe was used to obtain planes of mean velocity measurements. A three-component state of the art laser-Doppler velocimeter (LDV) was used to obtain mean and fluctuating velocities. Previous high free-stream turbulence studies have been reviewed and are discussed, and some of the previously published data of other authors have been corrected. Based on the measurements obtained with the LDV, it was also determined that the semi-log law of the wall is valid for high free-stream turbulence cases, but with different constants than the ones proposed by Coles, where the constants for the high free-stream cases may be dependent on the turbulence intensity. For the first time, the skin friction coefficient (Cf) was deduced from the viscous sublayer. The difference between the U_tau obtained in the viscous sublayer mean velocity profile and the U_tau obtained in the semi-log layer was 1.5%. The skin friction coefficient was determined to increase by 10.5% when the two-dimensional turbulent boundary layer was subjected to high free-stream turbulence effects. Spectral data obtained with the LDV, were compared to the von K&#225;rm&#225;n model spectrum and to the Pope's model spectrum, where the von K&#225;rm&#225;n spectrum was proven to fit the spectral data slightly better than the Pope's spectrum. Finally, the Hancock-Bradshaw-Blair parameter obtained for this experiment agreed very well with previously published data. / Master of Science

Fluid dynamicists are always in need of innovative instruments for flow velocity measurements. An ideal instrument would be non-intrusive, have a very fine spatial resolution as well as a very fine temporal resolution, be able to measure three-components of velocity, and be compact. Through recent advancements, laser Doppler velocimetry can now meet all of those requirements making it an important part of aerodynamicist's research toolbox. The first paper presented in this manuscript style thesis explains the development of an advanced three-velocity component, spatially-resolving laser-Doppler velocimetry (LDV) system for highly resolved velocity measurements in situations with limited optical access. The new instrument, a next generation version of the previously developed 'comprehensive' LDV technology, enables measurements of three components of velocity and particle position in the axial direction all through a single transceiving lens. Described here is the design process and the final design for the 'compact, comprehensive' LDV (Comp²LDV). The probe was designed to achieve ± 10 micron root-mean-square uncertainties in axial particle position, which combined with the long measurement volume, allow researchers to obtain a three-velocity-component velocity statistics profiles over a span of approximately 1.5mm without the need for traversing. Results from measurements in a flat plate turbulent boundary layer very near the wall have compared favorably to data from previous studies. The second paper focuses on the motion and evolution of coherent structures in supersonic jet flows and how that relates to the intense noise the flows generate. As a preliminary study to experimentally address these relationships, novel non-intrusive measurements using two-component laser Doppler velocimetry (LDV) have been conducted at exceptionally high data rates to lend insight into the statistical behavior of noise-generating flow structures. A new heated supersonic jet facility has been constructed to provide supersonic flow at total temperatures ratios (T₀/Tₐ) up to 3. In the present work, the instrumentation is validated via comparison of LDV measurements along the centerline of a screeching cold jet with microphone and high-speed shadowgraph results. Reynolds stress spectra are presented for an over-expanded case (nozzle pressure ratio of 3.2) of a design Mach number 1.65 nozzle operated cold (T₀/Tₐ = 1). A preliminary study was then conducted in the near-nozzle shear layer, up to x/d = 4.0, at design nozzle pressure ratio (4.58) and total temperature ratio of 2.0. Results are presented for Reynolds stress time-delay correlations and power spectra at Re_d = 1.1M for this case. The stream-wise Reynolds normal stress spectra are compared with published spectral behavior reported by other researchers, indicating a similar spectral shape in the downstream stations as previously measured with LDV and hot wire anemometry for cold jets, but which differ in shape from density-based techniques. / Master of Science