Nadir Dagli. / Also issued as Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Electrical Engineering and Computer Science, 1987. / Includes bibliographical references. / Supported in part by the Joint Services Electronics Program. DAAL03-K-0002 Supported in part by the National Science Foundation. ECS-83-05448 Supported in part by the U.S. Army Research Center. P-23223-EL

Unsteady shock waves are formed by the coalescence of pressure waves. The attenuationof pressure and shock waves in general is of great importance in a wide varietyof application such as vehicle performance, health and safety. Previous researcheshave been carried out on a variety of geometries to understand the physics. Theaim of this project is to advance the previous-state-of-the-art and to shed furtherlight into the fundamental physics associated with the shock wave interactions andphenomena. Shock wave attenuation was studied by using rough walls in a three-pipe system. The roughness at the walls is added by placing grooves on the upper and lower wallsof the junctions. The angles of the branch pipe were varied from 30 to 150 degrees. Shock wave interactions with a co-flow jet were also examined. All the experimentswere performed for driver gas (air) pressures of 4, 8, and 12 bar and atmosphericpressure within the driven section, giving theoretical Mach number of 1.34, 1.54, and1.66, respectively. Three different velocities, 114, 138, and 178 m/s, were used forthe co-flow jet. High-speed schlieren photography, particle image velocimetry (PIV),and pressure measurements techniques were employed to visualise and quantify theflow field. Expansion and compression waves produced by the grooves led to a highly unsteadyflow field, an increase to the pressure upstream, and the formation of asecondary shock wave. The pressure of the incident shock front was reduced by anestimated 20%. A maximum of 10% reduction of velocity of the shock front at theexit was achieved. The shock vortex/ structure led to multiple reflections, distortionof the vortical field, a lambda-shock configuration and pressure fluctuations. Theinfluence of the co-flow jet dissipated the shock/vortex structure, and attenuatedthe pressure peaks caused by multiple reflections. Complementing this investigation the testing of pressure sensitive paints (PSP)for the use of unsteady and high speed flows was carried out. The results showedthat the use of luminophores with high intensity output, and pressure sensitivityapplied on a porous material were the most suitable PSPs for these applications.

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In this thesis, a numerical study of film cooling in hypersonic laminar and turbulent flows has been performed using an in-house Navier-Stokes solver. The aim of this computational work is to investigate the mechanism and effectiveness of film cooling in hypersonic laminar and turbulent flows. Hypersonic flow over a flat plate without film cooling was first studied to provide a reference datum to check the effectiveness of film cooling. For laminar film cooling (M¥ = 9.9), three different primary flow conditions were first used for validation. The inclusion of the development of the flow in the plenum chamber upstream of the slot was found to provide better heat prediction than a uniform boundary condition at the slot exit. Detailed information of the flow field including velocity profile, Mach contour, temperature contour and heat transfer rate was presented. The mechanism of film cooling has been revealed according to the plots of calculated velocity profiles, Mach contours and temperature contours downstream of the slot. The coolant fluid was found to affect the primary boundary layer in two ways: 1) initially a separate layer established by the coolant fluid itself in the near slot area, 2) later a mixing layer between the primary and coolant flow streams. Then five coolant injection rates between 2.95 x 10-4 and 7.33 x 10-4kg/s and three slot heights 0.8382, 1.2192, 1.6002 mm, were examined in hypersonic laminar film cooling. For turbulent film cooling (M¥ = 8.2), for the geometry used in the experiment, the injection at an angle of 20° was found to be appropriate. Different turbulence models including Wilcox's k - w model. Menter's baseline and SST model have been tested. It is concluded that the Wilcox's k - w turbulence model with dilatation-dissipation correction provides the best heat prediction. Again, five coolant injection rates varies from 5.07 x 10-4 to 30.69 x 10-4 kg/s and three slot heights (the same as studied in the laminar film cooling) were studied to check the influence on film cooling effectiveness. Both the coolant and the primary flow were air. Film cooling was found to be an effective way to protect wall surfaces that are exposed under a high heat transfer environment especially in hypersonic laminar flow. Increasing the coolant injection rate can obviously increase the film cooling effectiveness. Again, this works better in laminar flow than in turbulent flow. The coolant injection rate in turbulent flow should be considered to be high enough to give good heat protection. Slot height in both laminar and turbulent flows under the flow conditions in this study was found to be less important, which means other factors can be considered in priority when constructing film cooling systems. With the application of curve fitting, the cooling length was described using power laws according to curve fitting results. A two-equation film coating model has been presented to illustrate the relation between the film cooling effectiveness and the parameter x/(h/m). For film cooling effectiveness in log-log coordinates, a second-order polynomial curve can be used to fit the laminar flows, whilst a straight line is suitable for the turbulent flows.

Vorliegende Arbeit befasst sich mit dem Fortschritt der Qualitätssicherungsmaßnahmen des österreichischen Gesetzgebers einerseits und des Berufstandes andererseits im Bereich der Wirtschaftsprüfung. Dabei zeigt sich, dass dieser bis dato noch im Fluss ist und keineswegs als abgeschlossen erachtet werden kann. Der Autor gibt in seiner Arbeit einen Überblick über die jüngsten gesetzlichen sowie berufsständischen Entwicklungen, analysiert den status quo und zeigt auf, wo Verbesserungspotential besteht, um das Vertrauen in die Abschlussprüfung zu stärken. (Autorenref.)

Anemometers on Voluntary Observing Ships (VOS) are usually located above the bridge in a region where the effects of air flow distortion, created by the presence of the ship, may be large. Until now it was not known whether measurements from such anemometers would be biased high or low, and the possible magnitude of any such bias was not known. Investigations into the airflow above merchant ships have been carried out experimentally using a low-speed wind tunnel and numerically using a commercial Computational Fluid Dynamics (CFD) code VECTIS. The investigations examined the airflow over simple block models of VOS shapes. The results of the investigations were compared to wind speed measurements made from the RRS Charles Darwin. Experimental and CFD techniques have been used to devise scaling rules that predict the effects of the flow distortion. Both techniques have shown that the pattern of the flow distortion above the bridge scales with the ‘step height’, H, of the model. In the case of a tanker, H is the ‘bridge to deck’ height, i.e. the height of the accommodation block above the deck, for bow-on flows. Close to the top of the bridge the flow is severely decelerated and may even reverse in direction. Using the upwind edge of the bridge as the origin of the scaled co-ordinate system, there is a definite line above the decelerated region along which the speed of the flow is equal to the undistorted wind speed. Above this ‘line of equality’ the wind speed increases to a maximum and then decreases with increased height to a free stream wind speed. Simple equations have been devised to predict the positions of the ‘line of equality’, the maximum wind speed and the minimum wind speed within the decelerated region. Comparisons of the results with wind speed data obtained from field measurements made using a number of anemometers located on the RRS Charles Darwin agreed well and have predicted a maximum wind speed increase of approximately 15 ±5 %. Comparisons with the field data have confirmed that CFD models can be used to predict the effects of airflow distortion above merchant ships. The investigation has demonstrated the ability of the wind tunnel and CFD approaches employed to provide a better understanding of the airflow over merchant ships. Both methods have contributed to improve the understanding of how the wind speed at anemometer sites on merchant ships is affected by the ships hull and superstructure.

Für die Herstellung von immer kleiner werdenden elektronischen Bauteilen ist es notwendig, Schichten verschiedener Stoffe auf einem Substrat abzuscheiden. Dazu werden häufig Verfahren verwendet, bei denen Gase in kleine Strukturen eindringen und dort an der Oberfläche reagieren. Damit können Schichten abgeschieden werden. Bei der Gasströmung in mikroskopischen Strukturen auf einem Wafer zeigt sich ein anderes Strömungsverhalten als bei einer Gasströmung in einer makroskopischen Struktur bei Normaldruck. Dabei sind Kollisionen zwischen Gasteilchen oft vernachlässigbar, und die Kollisionen von Teilchen mit der Geometrie, in der sich das Gas befindet, überwiegen. Zur Untersuchung solcher Vorgänge ist es von Interesse, eine derartige Gasströmung und die entsprechenden Schichtabscheidungen simulieren zu können. In dieser Arbeit wurde ein Simulationsverfahren entwickelt, welches Gase im Bereich der freien Molekülströmung und deren chemische und physikalische Interaktionen an Oberflächen simulieren kann. Die Simulationen sind dabei speziell für die freie Molekülströmung optimiert und ist nicht auf viele Aspekte angewiesen, die in anderen Strömungsregimen notwendig sind. Dies geschieht mittels einer Monte-Carlo-Simulation von Teilchen, welche mittels Pfadverfolgung in einer beliebigen dreidimensionalen Geometrie simuliert werden können. Dabei kann eine große Menge an verschiedenen Wechselwirkungen von Teilchen mit den Wänden der Geometrie simuliert werden. Es erfolgten Vergleiche mit bekannten Literaturwerten, wie der Durchlasswahrscheinlichkeit eines Zylinders oder einem einzelnen ALD Schritt in einem zylinderförmigen Loch bei verschiedenen Adsorptionswahrscheinlichkeiten. Das verwendete Simulationsverfahren erlaubt eine einfache Erweiterung von Wechselwirkungen, welche an Oberflächen auftreten können. So wurde auch ein PVD Verfahren und der Einfluss eines Kollimators auf die Teilchenströmung untersucht.:Inhaltsverzeichnis Abbildungsverzeichnis Tabellenverzeichnis Abkürzungsverzeichnis Symbolverzeichnis 1 Motivation und Einführung 2 Grundlagen 2.1 Knudsenzahl 2.1.1 Strömungsregime 2.1.2 Mittlere freie Weglänge bei verschiedenen Teilchenarten 2.2 Schichtabscheidungen 2.2.1 Chemische Gasphasenabscheidung 2.2.2 Atomlagenabscheidung 2.2.3 Physikalische Gasphasenabscheidung 2.3 Chemische Reaktionen an Oberflächen 2.3.1 Adsorption an einer freien Oberfläche 2.4 Simulationsansätze 2.4.1 Direct Simulation Monte Carlo 2.4.2 Angular Coefficient Method 2.4.3 Pfadverfolgung von Teilchen 2.4.4 Finite Volumen Methoden 3 Modellentwicklung 3.1 Grundidee 3.2 Interaktionen an Wänden 3.2.1 Reflexion und Reemission von Teilchen 3.2.2 Chemische Reaktionen 3.2.3 Tabellierte Oberflächeninteraktionen 3.3 Erweiterung für Bereiche geringerer Knudsenzahlen 3.4 Implementation 3.4.1 Wandkollisionen 3.4.2 Raytracing und Unterteilung der Geometrie 3.4.3 Simulationsdefinition 3.4.4 Simulationen in 2D 4 Simulationen und Ergebnisse 4.1 Durchlasswahrscheinlichkeit eines Hohlzylinders 4.2 Durchlasswahrscheinlichkeit durch ein gekrümmtes Rohr in 2D 4.3 ALD in einem zylinderförmigen Loch 4.4 Gleichgewicht zwischen Adsorption und Desorption an einer Oberfläche 4.5 Sputterabscheidung von Kupfer in einem PVD-Reaktor 4.5.1 Simulationen in einem Vakuum 4.5.2 Simulation bei Verwendung eines Hintergrundgases 5 Zusammenfassung und Ausblick 5.1 Zusammenfassung 5.2 Ausblick Literaturverzeichnis Danksagung Selbstständigkeitserklärung

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Στη παρούσα διπλωματική εργασία μελετήθηκε, σχεδιάστηκε, προσομοιώθηκε και κατασκευάστηκε ένα σύστημα ενός ταλαντωτή το οποίο μειώνει τον θόρυβο φάσης (phase noise) σε εικονικά οποιονδήποτε ήδη υπάρχον ταλαντωτή ελεγχόμενου από τάση (VCO). Για να το πετύχει αυτό η προτεινόμενη τεχνική δανείζεται από την ιδέα του βρόχου κλειδωμένης φάσης (Phase Locked Loop) και με λίγα επιπλέον ηλεκτρονικά στοιχεία καθιστά δυνατή την μείωση του phase noise επηρεάζοντας σε μικρό βαθμό τα χαρακτηριστικά του VCO αλλά και δίνοντας την δυνατότητα παραμετροποίησης των χαρακτηριστικών ποιοτικών στοιχείων του τελικού ταλαντωτή που προκύπτει. Το σύστημα του ταλαντωτή κατασκευάστηκε σε πλακέτα(PCB) με διακριτά στοιχεία τα οποία παρέχονταν από το Εργαστήριο Ηλεκτρονικών Εφαρμογών. Το σύστημα αυτό μπορεί να ανταποκριθεί στις ραγδαία αυξανόμενες απαιτήσεις απόδοσης των ταλαντωτών στις σημερινές εφαρμογές, όσο αφορά στον χαμηλό θόρυβο φάσης, την χαμηλή κατανάλωση, την μικρή πολυπλοκότητα στο σχεδιασμό, την μικρή επιφάνεια και την ευκολία στην ολοκλήρωση. / The present diploma thesis pertains the study, design, simulation and implementation of an oscillator system that reduces phase noise in virtually any given already existing voltage controlled oscillator (VCO). To achieve that the proposed technique borrows from the idea of the Phase Locked Loop and with just a few extra electronic components it enables the reduction of phase noise ,by affecting the core characteristic qualities of the employed VCO only by a small fraction, as well as the optimization of the specifications of the resulting oscillator. This oscillator system was manufactured on a printed circuit board and implemented with discrete components which were supplied by the Applied Electronics Lab. This system can measure up to the increasing performance demands for oscillators by todays applications in terms of low phase noise, low power consumption, small design complexity, small area and ease of integration.