Cinematographic stereoscopic PIV, combined with Taylor's frozen flow hypothesis, is used to generate three-dimensional (3D) quasi-instantaneous pseudo volumes of the three-component (3C) velocity field in the far field of turbulent nonpremixed jet flames at jet exit Reynolds number Reδ in the range 8,000-15,300. The effect of heat release, however, lowers the local (i.e., based on local properties) Reynolds number to the range 1,500-2,500. The 3D data enable computation of all nine components of the velocity gradient tensor ∇u from which the major 3D kinematic quantities, such as strain rate, vorticity, dissipation and dilatation, are computed. The volumetric PIV is combined with simultaneously acquired 10 Hz OH planar laser-induced fluorescence (PLIF). A single plane of the OH distribution is imaged on the center-plane of the volume and provides an approximate planar representation of the instantaneous reaction zone. The pseudo-volumes are reconstructed from temporally and spatially resolved kilohertz-rate 3C velocity field measurements on an end-view plane (perpendicular to the jet flame axis) invoking Taylor's hypothesis. The interpretation of the measurements is therefore twofold: the measurements provide a time-series representation of all nine velocity gradients on a single end-view plane or, after volumetric reconstruction, they offer a volumetric representation, albeit approximate, of the spatial structure of the flow. The combined datasets enable investigation of the fine-scale spatial structure of turbulence, the effect of the reaction zone on these structures and the relationship between the jet kinematics and the reaction zone. Emphasis is placed on the energy dissipation field and on the presence and role of dilatation. Statistics of the components of the velocity gradient tensor and its derived quantities show that these jet flames exhibit strong similarities to incompressible turbulent flows, such as in the distribution of the principal strain rates and strain-vorticity alignment. However, the velocity-gradient statistics show that these jet flames do not exhibit small-scale isotropy but exhibit a strong preference for high-magnitude radial gradients, which are attributed to regions of strong shear induced by the reaction zone. The pseudo volumes reveal that the intense-vorticity field is organized in two major classes of structures: tube-like away from the reaction zone (the classical worms observed in incompressible turbulence) and sheet-like in the vicinity of the local reaction zone. Sheet-like structures are, however, the dominant ones. Moreover, unlike incompressible turbulence where sheet-like dissipative structures enfold, but don't coincide with, clusters of tube-like vortical structures, it is observed that the sheet-like intense-vorticity structures tend to closely correspond to sheet-like structures of high dissipation. The primary reason for these features is believed to be due to the stabilizing effect of heat release on these relatively low local Reynolds number jet flames. It is further observed that regions of both positive and negative dilatation are present and tend to be associated with the oxidizer and fuel sides of the OH zones, respectively. These dilatation features are mostly organized in small-scale, short-lived blobby structures that are believed to be mainly due to convection of regions of varying density rather than to instantaneous heat release rate. A model of the dilatation field developed by previous researchers using a flamelet approximation of the reaction zone was used to provide insights into the observed features of the dilatation field. Measurements in an unsteady laminar nonpremixed jet flame where dilatation is expected to be absent support the simplified model and indicate that the observed structure of dilatation is not just a result of residual noise in the measurements, although resolution effects might mask some of the features of the dilatation field. The field of kinetic energy dissipation is further investigated by decomposing the instantaneous dissipation field into the solenoidal, dilatational and inhomogeneous components. Analysis of the current measurements reveals that the effect of dilatation on dissipation is minimal at all times (it contributes to the mean kinetic energy dissipation only by about 5-10%). Most of the mean dissipation arises from the solenoidal component. On average, the inhomogeneous component is nearly zero, although instantaneously it can be the dominant component. Two mechanisms are believed to be important for energy dissipation. Near the reaction zone, where the stabilizing effect of heat release generates layers of laminar-like shear and hence high vorticity, solenoidal dissipation (which is proportional to the enstrophy) dominates. In the rest of the ow the inhomogeneous component dominates in regions subjected to complex systems of nested vortical structures where the mutual interaction of interwoven vortical structures in intervening regions generates intense dissipation. / text

Wingtip vortices, created as a byproduct of lift, are both a hazard and a significant limiting factor in the increase of air traffic. In order to reduce separation distances between airplanes and increase safety, active flow control solutions are considered, however, more research is required to better understand the behavior of wingtip vortices. Therefore, this research focuses on the modification of the flow structure downstream using pulsed jets, visualization of the behavior of wingtip vortices using two dimensional particle image velocimetry, as well as measurements of the forces and moments affected by the pulsed jets using an aerodynamic balance. A NACA 0012 wing model equipped with two slots was mounted in a wind tunnel at approximately 150,000 Reynolds number. A valve system was designed to create jets of air at the wing tip in a steady or pulsed pattern from a slot placed either on the pressure side or the suction side. Particle image velocimetry measurements were taken at various distances downstream, and post-processed for the characterization of the vortex : position, angle, distance, vorticity contour, and circulation. Results indicate that the vortex can be forced into a cyclic pattern constrained between the baseline (no jet) vortex core position, and the position when the jet is permanently activated (steady blowing cases). Depending on the slot used, the vortex trajectory can be forced into an inclination angle. Steady blowing cases show near-sinusoidal oscillations, while pulsed blowing cases exhibit a steady rise in angle, with a slight oscillating pattern in displacement distance values. The circulation values are significantly changed, with a significantly higher dispersion than for the baseline case. Furthermore, the vortex core size is consistently larger as it is displaced away from the baseline case. Additionally, lift, drag and pitching moment were measured in a wind tunnel using an aerodynamic balance. Results showed that lift/drag coefficients consistent with published results, and that activating the jets on the pressure or suction side decreased lift. As instability grows, the destruction of the wingtip vortices occurs past the maximum downstream distance studied, therefore, additional PIV measurements should be taken further downstream. Moreover, supplementary PIV measurements at the slot themselves should be considered to better understand how the perturbed flow structure interacts with the pulsed jets.

The effects of simulated battle damage on the aerodynamic performance of a wing is well documented; it is known that battle damage reduces lift, increases drag and changes pitching moment. However, there is a fundamental lack of understanding when it comes to the three-dimensional flow features that create such effects. The current knowledge of the flow field is predominantly based upon interpretation of surface flow visualisation techniques coupled with force balance measurements. In this work, a more modern technique in the form of Particle Image Velocimetry (PIV) has been used to map the three-dimensional flow field away from the wing surface. A PIV system was designed for the Loughborough University Low Turbulence Wind Tunnel in order to gain a deeper understanding of the flow mechanisms that are produced by simulated battle damage. The system was tested for suitability and the data quality assessed. The system was found to produce high quality vector output with low levels of uncertainty, it could also be used in multiple planes and orientations to provide the flow field data required. The technique was first applied to a single battle damage hole with a diameter of 20% chord, located at the wing s mid-chord. The wing model was of realistic construction and had a cavity. This damage case had previously been shown to produce different flow features across the incidence range and was typically a survivable damage case. The hole was seen to produce a jet at incidence angles above 2°, however the characteristics of the jet were different to those predicted in previous battle damage work and in jets in cross-flow research. The velocity ratio was very low peaking at around 0.25 at 8° incidence, much lower than the surface flow features and jet in cross-flow literature would suggest. No characteristic counter-rotating vortex pair was found in the jet due to the presence of a wing cavity and low velocity ratio. It is suggested that the wing's adverse pressure gradient has a magnified effect on the wake and is responsible for the increase in wake size at higher incidence angles, something previously thought to be due to increasing velocity ratio. A larger hole of 40% chord located at mid-chord, along with a straight through damage hole with no cavity, have been tested to isolate and highlight flow features to further explain the flow mechanics. Then, PIV was applied to several multiple hole damage cases to study the interaction caused by such damage. Side-by-side holes with different proximities, where the two damage holes had the same chordwise location, were studied to isolate interaction effects. It was found that at low incidence angles the force increments were double that of a single damage hole at the same chordwise location. However, as incidence angle increased above 2° the increments were less than double. This was because the wakes of the two damage holes were smaller than the wake of a single damage hole. From a purely aerodynamic point of view, it was seen that having two holes close together interacting was favorable compared with having two holes far apart with no interaction. Two in-line damage holes were also tested. Once again the two holes together produced smaller increments than predicted by the summation method, i.e. summing the increments created by each single hole tested individually. The presence of two holes in-line limited the effectiveness of the forward hole and hence limited the performance losses, whereas individually the hole at the forward chord location will produce much larger effects than an equivalent hole further aft.

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.

Gibbsite scale growth in pipe fittings is a major problem for an alumina refinery. A recent investigation into the scale growth mechanism at an alumina refinery found almost 60 % more scale growth in a reducer when compared with the connecting straight pipe sections for similar flow conditions. Scale growth occurs where liquor (supersaturated solutions) come in contact with solid surfaces and it is affected by the liquor flow velocity besides other physical and chemical parameters. The present work is dedicated to study the hydro-dynamical aspects of the mechanism of scale growth. In particular, the role of the phenomenon of turbulent bursting, stream wise and cross stream fluctuating velocity components (Ux and Uy) was investigated as the flow moves through the reducer. Particle Image Velocimetry (PIV) technique was used to get a full view of the reducer and the readings close-to-the-wall of the reducer at Reynolds number of 27,000 and 44,000 upstream which corresponds to Reynolds number of 41,500 and 66,000 downstream of the reducer respectively. The results showed an increase in cross stream and a decrease in magnitude of stream wise fluctuating velocity components, whereby we presume that the increased cross stream fluctuating velocity component increases the frequency of impacts of the scaling particles on the wall thus initiating excessive scale growth in the reducer when compared with the connecting straight pipe sections, for similar flow conditions.

The overarching objective of this research project was to gain improved basic understanding of the fluid mechanisms governing the development of secondary flow structures in complex, three-dimensional inlet ducts. To accomplish this objective, particle image velocimetry measurements were employed to document the mean and turbulent flow properties within the complex flow regions. Complimentary, surface oil flow visualizations and static pressures were obtained to aid in the interpretation of the PIV data. Using these diagnostic techniques, the formation of a pair of counter-rotating vortices was revealed. Two-dimensional PIV measurements were conducted along 20 planes near the two bends of the duct model. All data was collected with an incoming freestream of 40 m/s. Over 2000 image pairs were collected for each measurement location, which were then processed and averaged to generate mean velocity, variance intensity, and velocity gradient statistics. The data was analyzed and it was determined that the experimental PIV data corresponded well with the qualitative flow visualization. This research will contribute to the particle image velocimetry database and subsequent analyses, which will provide additional insight into the flow structure and provide a new database for numerical model validation.

The overarching objective of this research project was to gain improved basic understanding of the fluid mechanisms governing the development of secondary flow structures in complex, three-dimensional inlet ducts. To accomplish this objective, particle image velocimetry measurements were employed to document the mean and turbulent flow properties within the complex flow regions. Complimentary, surface oil flow visualizations and static pressures were obtained to aid in the interpretation of the PIV data. Using these diagnostic techniques, the formation of a pair of counter-rotating vortices was revealed. Two-dimensional PIV measurements were conducted along 20 planes near the two bends of the duct model. All data was collected with an incoming freestream of 40 m/s. Over 2000 image pairs were collected for each measurement location, which were then processed and averaged to generate mean velocity, variance intensity, and velocity gradient statistics. The data was analyzed and it was determined that the experimental PIV data corresponded well with the qualitative flow visualization. This research will contribute to the particle image velocimetry database and subsequent analyses, which will provide additional insight into the flow structure and provide a new database for numerical model validation.

No description available.

Enhancing the performance of mixing and fluid entrainment by excitation of quasi-steady jets has been a subject of research for more than three decades. During the 1980s a special emphasis was placed on mechanically oscillating planar jets and the possibility to augment thrust of V/STOL aircraft. However, during this time, little attention was paid to the classification of flow regimes, the development of coherent structures or the existence of different regions in the flow within the jet near field. For the present study, a large aspect ratio nozzle was oscillated in the direction transverse to the width of the nozzle in simple harmonic motion. For a constant nozzle height, the stroke length, oscillation frequency and jet velocity were systematically varied. Over 240 flow cases were examined using a novel method of phase-locked flow visualisation. Following an initial analysis of the acquired data, a small subset of flow conditions was selected for further quantitative investigation using Particle Image Velocimetry (PIV). The phase-locked flow visualisation led to the identification and classification of three separate flow regimes, the Base Flow, the Resonant Flow and the Bifurcation Flow Regimes. Each regime is linked to the other regimes by the presence of a small number of repetitive coherent structures in the form of starting and stopping vortices. The analysis revealed a relationship between the stroke-to-nozzle height ratio and the ratio of the forcing frequency to the natural vortex shedding frequency in the planar jet. This directly contradicts the relationship between the Strouhal and Reynolds numbers of the jet that was proposed by previous investigators. Comparison of phase-locked PIV and flow visualisation data confirms both, the validity of the new regime classification and the identification of relevant large-scale structures. Time-averaged vorticity data are also used to further illustrate the differences between the three flow regimes. Investigation of the time-averaged qualitative data for the Base and Resonant Flow Regimes show that three distinct flow regions exist within both regimes. Adjacent to the nozzle is the initial formation region, where all large-scale structures form. This is followed by a coherent near-field region in which the jet exhibits very little spread for both the Base and Resonant Flow Regimes. Within this region no pairing of the large-scale vortices from the opposing sides of the flow can be found. This region is followed by a transition region that is marked by the sudden breakup and dissipation of all visible large-scale coherent structures. The vortex formation distance is then investigated using the available PIV data and compared with the results of previous investigations. The data show that the formation distance depends on the jet velocity, oscillation frequency and the stroke length. The agreement with previous data is poor due to differences in the method of measurement. Quantitative data are also used to investigate the centreline velocity decay in relation to changes of the jet Reynolds number and stroke-to-nozzle height ratio. The results show that the velocity decay rate increases with increasing stroke length as is expected from findings of earlier studies. In addition the centreline velocity decay rates in the mean jet transition region appear to be constant for each stroke length in the cases examined. Finally, conclusions are drawn and recommendations for future work are presented. / http://proxy.library.adelaide.edu.au/login?url= http://library.adelaide.edu.au/cgi-bin/Pwebrecon.cgi?BBID=1349701 / Thesis (Ph.D.) -- University of Adelaide, School of Mechanical Engineering, 2009

The human upper airway structure provides access of ambient air to the lower respiratory tract, and it as an efficient filter to cleanse inspired air of dust bacteria, and other environmental pollutants. When air passes through airway passages, it constantly changes direction, which may lead to flow separation, recirculation, secondary flow and shear stress variations along the airway surface. Therefore, it is essential to understanding the air transport processes within the upper airway system. The functions are respiratory defence mechanisms that protecting the delicate tissues of the lower airway from the often harsh conditions of the ambient air. While protecting the lower respiratory system, however, the upper airway itself becomes susceptible to various lesions and infections from filtration of environmental pollutants. Inhaled particle pollutants have been implicated as a potential cause of respiratory diseases. In contrast, inhalation of drug particles de posited directly to the lung periphery results in rapid absorption across bronchopulmonary mucosal membranes and reduction of the adverse reactions in the therapy of asthma and other respiratory disorders. For this purpose, it is desirable that the particles should not deposit in the upper airways before reaching the lung periphery. Therefore, accurate prediction of local and regional pattern of inhaled particle deposition in the human upper airway should provide useful information to clinical researchers in assessing the pathogenic potential and possibly lead to innovation in inhalation therapies. With the development of the increasing computer power and advancement of modeling software, computational fluid dynamics (CFD) technique to study dilute gas-particle flow problems is gradually becoming an attractive investigative tool. This research will provide a more complete picture of the detailed physical processes within the human upper airway system. Owing to the significant advancements in computer technologies, it will allow us to efficiently construct a full-scaled model integrating the various functional biological elements including the nasal, oral, laryngeal and more generations of the bifurcation of the human upper airway system through imagining methodologies. A significant advantage of this human model is that the differences in airway morphology and ventilation parameters that exist between healthy and diseased airways, and other factors, can be accommodated. This model will provide extensive experimental and numerical studies to probe significant insights to the particle deposition characte ristics within the complex airway passages and better understanding of any important phenomena associated with the fluid-particle flow. It will also lead to an improved understanding of fluid/particle transport under realistic physiological conditions. New concepts and numerical models to capture the main features observed in the experimental program and innovative techniques will be formulated. The ability to numerically model and a better physical understanding of the complex phenomena associated with the fluid dynamics and biological processes will be one of the major medical contributions especially targeting drug delivery and health risk analysis. Its biomedical engineering significance lies in the fact that this will enable us to accurately evaluate potential biological effects by the inhaled drug particles, facilitating new drug research and development.