No description available.

A study of the squish-jet design concept in spark ignition engines, with central ignition, was conducted in a constant volume chamber. The effects of jet size, jet number and jet orientation in generating turbulence and jet enhanced turbulent combustion were investigated. Three sets of configurations with three port sizes were used in this study. The research was carried out in three stages: 1.Qualitative information was obtained from flow visualization experiments via schlieren photography at 1000 frames per second. The flow medium was air. A sequence of frames at specific time intervals were selected to study the results from the respective configurations and jet sizes. The swirling nature of the flow is vivid in the offset arrangement. 2.Pre-ignition pressure and combustion pressure traces were measured with a piezoelectric pressure transducer from which characterising parameters such as maximum pressure, ignition advance and mass burn rate were analysed. Mass fraction curves were calculated using the simple model of fractional pressure rise. A maximum pressure increase of 66% over the reference quiescent combustion case, and combustion duration reduction of 77% were obtained for the offset arrangement with 2 mm diameter port. Comparisons of the times required for 10%, 50% and 90% mass burned are identified and confirmed that it took the 2 mm jet the shortest time to burn 90% of the mixture in the chamber. 3.Two-component velocity measurements were made using an LDV system. Measurements were taken in the central vertical plane of the chamber at specified locations. The data collected were window ensemble- averaged for the mean and fluctuating velocities over a number of cycles. Data intermittency and low data rate precluded, however, cycle-by-cycle analysis. Mean tangential velocities were calculated for each case and the data were used to construct a movie of the tangential velocity as a function of time, suitable for quantitative flow visualization. The vortical nature of the flow was recorded, the distribution being neither solid body rotation nor free vortex, but some complex fluid motion. The jet scale and orientation influence the in generation of turbulence flow field in the chamber, affecting the rate of combustion and the ensuing maximum pressure rise. The offset jet arrangement gives the best results, whereas radially opposed jets have a reduced effect. Increasing the number of jets in opposed arrangement does not enhance turbulent flow. Turbulent flow in the spark region during the onset of ignition was found to be important. / Applied Science, Faculty of / Mechanical Engineering, Department of / Graduate

L’émission de HAPs (Hydrocarbures Aromatiques Polycycliques) et de particules carbonées produis lors de la combustion d’hydrocarbures ont un impact important à la fois sur l’environnement et sur la santé. En effet, les particules de suie, étant des particules ultra-fines sont facilement assimilées par le système respiratoire et provoquent des troubles de l’organisme. De plus, les HAPs que ce soit en phase gazeuse ou adsorbés à la surface des suies sont reconnus comme étant des composés mutagènes et cancérigènes. La limitation des émissions de ces espèces polluantes passe par une compréhension des mécanismes à l’origine de leur formation et nécessite donc la mise en place de techniques de plus en plus sensibles pour permettre leur détection dans des flammes où évoluent de nombreuses espèces chimiques en interaction les unes avec les autres. Ce travail de thèse a donc pour objectif de développer une nouvelle méthode de détection de HAPs sélective, sensible et quantitative reposant sur l’extraction des espèces de la flamme et à leur analyse par Fluorescence Induite par laser (LIF) après refroidissement au sein d’un jet supersonique. Cette stratégie conduit à l’obtention de spectres caractéristiques de HAPs spécifiques permettant ainsi leur mesure quantitative et sélective. Grâce au développement de cette méthode, la mesure de profils de fraction molaire de trois espèces clefs dans les mécanismes de formation des HAPs (benzène, naphtalène et pyrène) a pu être réalisée dans une flamme de prémélange CH4/O2/N2 stabilisée à basse pression pour différentes conditions de pression et de richesse. En parallèle, les profils de fraction volumique de suie ont été obtenus in situ par la technique d’Incandescence Induite par Laser (LII), ce qui a permis de dégager des corrélations entre concentrations de HAPs et de particules de suie. La base de données obtenue permettra d’affiner les modèles cinétiques de formation de HAPs et de suies dans les flammes. / The emission of PAHs (Polycyclic Aromatic Hydrocarbons) and carbonaceous particles produced during fuel combustion have a significant impact both on the environment and health. Indeed, soot particles, as ultra-fine particles are easily assimilated by the respiratory system and cause disorders of the body. In addition, PAHs either in the gas phase or adsorbed on the surface of soot are known to be mutagenic and carcinogenic compounds. Understanding of these pollutants formation requires the development of more and more sensitive techniques to allow their detection in flames, a complex environment where many chemical species interact. This thesis aims to develop a new selective, sensitive and quantitative method for detecting PAHs based on the extraction of flame species and their analysis by Laser Induced Fluorescence (LIF) after cooling within a supersonic jet. By using this method, it is possible to obtain selective spectra of individual PAHs allowing their selective and quantitative measurement in flames.With the development of this method, the measurement of mole fraction profiles of three key species in the mechanisms of PAHs formation (benzene, naphthalene and pyrene) was achieved in a CH4/O2/N2 laminar premixed flame stabilized at low pressure for different pressure and equivalence ratio conditions. In parallel, soot volume fraction profiles were measured in situ using the technique of Laser-Induced Incandescence (LII), highlighting correlations between concentrations of PAHs and soot particles. The obtained database will be useful to develop kinetics modelling of PAHs and soot formation in flames.

Ces travaux de recherche sont consacrés à l’étude des effets de température sur le développement aérodynamique et l’acoustique rayonnée d’un jet subsonique par simulation des grandes échelles. Ces simulations sont réalisées avec un solveur 3D résolvant les équations de Navier-Stokes compressibles par une approche Volumes Finis. De plus, des schémas de discrétisation spatiale et d’intégration temporelle peu dissipatifs et peu dispersifs sont utilisés pour permettre l’étude des phénomènes acoustiques. La propagation acoustique est réalisée grâce à l’analogie acoustique de Ffowcs-Williams et Hawkings.Dans un premier temps, une configuration de jet simple est étudiée. Deux points de fonctionnement sont simulés. Dans les deux simulations, la vitesse d’éjection est fixée avec un nombre de Mach acoustique M=0.9 et seule la température du jet est modifiée. Pour les deux simulations les nombres de Reynolds sont supérieurs à 105. Pour valider la méthodologie de calcul, l’aérodynamique et l’acoustique ont été comparées avec succès à des données expérimentales. Une étude plus approfondie sur les effets induits par la température sur la distribution azimutale et l’émergence de nouvelles sources acoustiques est également menée. Dans un second temps, une tuyère représentative de l’arrière corps de moteur d’avion civil est considérée. La méthodologie de calcul appliquée sur cette géométrie est identique à celle utilisée sur les jets simples flux. Deux simulations sont réalisées en gardant les vitesses d’éjection constantes et en ne modifiant uniquement la température d’éjection du flux primaire (multipliée par un facteur 2). Les différences observées entre les deux simulations sont moins importantes que pour le cas simple flux. Cependant, le rayonnement acoustique amont est influencé significativement par la différence de température. Dans le cas froid, des ondes acoustiques remontant l’écoulement sont observées au centre du jet et rentrent en interaction avec le corps central. Ce phénomène n’est pas observé pour le cas le plus chaud, expliquant ainsi les différences sur le rayonnement acoustique. / In this PhD thesis, the effects of temperature on aerodynamic development and acoustic radiation of subsonic jets are studied. This is done thanks to 3D compressible Large Eddy Simulations with low dissipative and dispersive numerical schemes that propagate the acoustic waves properly. The far-field noise is then determined with the acoustics analogy proposed by Ffowcs-Williams and Hawkings.First, single round jets are studied. Two operating points are computed: an isothermal jet and a hot jet with an exhaust temperature twice the one of the ambient air (Tj = 2T0). The comparison of both cases is based on a similar exhaust velocity. In both cases, Reynolds number based on the nozzle diameter is above 105. To validate numerical methodology, aerodynamic and acoustic results are successfully compared against experiments. Further analyses are conducted to highlight the new acoustic sources that result from the temperature increase and the effects on the azimuthal mode distribution.Secondly, a more complex geometry representative of a real turbofan engine is considered, including two streams and the plug. The same methodology as the one used for the single jet nozzle is applied. Again, two simulations are computed where the exhaust velocities of both streams are kept constant and only the exhaust primary stream temperature is modified (multiplied by two). Differences on aerodynamic development are less important than the ones observed on single stream jets. However, the upstream acoustic radiation is significantly influenced by the modification of the exhaust temperature. In the colder case, upstream acoustic trapped waves are evidenced in the core jet and interact with the plug. This phenomenon is not reproduced when the primary stream is heated and explains the observed differences on the acoustic radiation.

<div> <p>Combustion will likely continue to be utilized over the next century to meet the world’s energy needs. As increasingly stringent requirements on emissions, particularly of oxides of nitrogen (NO and NO₂) are imposed on power plants due to their harmful effects on the environment, advanced combustor strategies to limit NO_X productions are needed. One such advanced concept involves axially staging the fuel to create a distributed combustion system. The fundamental problem for staged combustion involves the injection of a reacting jet into crossflow. This canonical problem is modified for this dissertation through injection of a reacting premixed natural gas and air jet into a compressible vitiated crossflow with negligible swirl. In addition, the experimental efforts for this work were conducted at elevated inlet air temperature and combustor pressure.</p><p>The development and performance of a perforated plate burner (PPB) to provide vitiated crossflow and operating using premixed natural gas (NG) and air at engine-relevant conditions is discussed. A significant benefit of using burners with simplified flow fields, such as the PPB, for experimental studies in the laboratory is the potential for decoupling the complex fluid dynamics in typical combustors from the chemical kinetics. The stable operation of the PPB within a high-pressure test rig was validated: successful ignition, effective use of redlines for flashback mitigation, and long duration steady-state operation in both piloted and non-piloted modes were all observed. Exhaust gas emissions measured using a Fourier-transform infrared (FTIR) spectrometer showed very good performance of the PPB in terms of the combustion efficiency and low levels of NO_X<i> </i>in non-piloted operation that were generally within 3 ppm.</p><p>Emissions measurements of the premixed reacting jet in vitiated crossflow were obtained for a variety of conditions and a significant NO_X reduction was achieved when the staged combustor exit Mach number was increased and the axial residence time was decreased. Based on this preliminary investigation, a test matrix was developed to independently vary the exit Mach number for a constant axial residence time by using modular rig hardware to change the length of the axial combustor. Up to 70% reduction in NO_X produced by the axial stage was observed when the combustor exit Mach number was increased from about 0.26 to 0.66 at a constant residence time of 1.4 ms. NO_X reduction based on variation in the Mach number and at a constant residence time has not been previously reported in the literature to the best of our knowledge. This decrease in NO_X is hypothesized to be due to the lower static temperature of a compressible flow and potentially better mixing of the jet with the crossflow due to the interaction occurring at high speeds.</p><p>Based on the strong effect of Mach number for NO_X reduction even at a constant residence time, further investigation using laser-based diagnostics is needed to provide insight on physical processes controlling this phenomenon. An optically-accessible secondary combustion zone was developed and fabricated to study the flame position and structure of reacting jets injected into a high-speed vitiated crossflow. The windowed combustor was capable of long-duration, steady-state operation despite a trifecta of: elevated pressures, high combustion gas temperatures, and high-speed reacting flows. High-speed imaging using OH* and CH* chemiluminescence was used to validate operation of the optically-accessible secondary combustion zone.</p><p>High-repetition-rate (1 – 10 kHz) planar laser-induced fluorescence (PLIF) imaging of OH and CH were performed on both premixed NG-air reacting jets and premixed NG-hydrogen-air reacting jets to investigate the flame structure of the reacting jet within a high-speed crossflow. OH-PLIF was performed in the A-X electronic system using excitation at near 283 nm in the (vʹ = 1, v″ = 0) band and near 311 nm in the (vʹ = 0, v″ = 0) band. The crossflow velocity and equivalence ratio were observed to have a strong impact on the stabilization of the reacting jet flame. Additional insight on the stabilization mechanism was obtained using 50 kHz OH* chemiluminescence imaging. CH-PLIF was performed in the C-X electronic system using R-branch excitation near 311 nm in the (vʹ = 0, v″= 0) band. The CH-PLIF images indicated local stoichiometric regions near the leeward side of jet injection and in regions where significant interaction of the fuel rich jet with the vitiated crossflow is expected. In addition, the CH-PLIF images showed evidence of broken, thickened, non-premixed reaction layers.<br></p></div>

No description available.

The objective of this dissertation was to investigate physical characteristics of high speed gas-liquid interfaces for the cases of subsonic, transonic, and supersonic gas jets submerged underwater and the transient development of an underwater projectile reaching the supercavitating state. These studies are motivated by the need to understand the basic physics associated with a novel submersible missile launcher termed the Water Piercing Missile Launcher (WPML). This dissertation presents the first study of high speed round and rectangular gas jets submerged underwater utilizing a global optical measurement technique. This technique allows quantitative measurement of the entire gas jet and the interfacial motion. Experimental results indicate that the penetration of the gas jets into a quiescent liquid is strongly influenced by the injection mass flow and the nozzle geometry. In contrast, the oscillations of the interface are influenced by the injection Mach number. The transition from a momentum driven to a buoyant jet is determined using a characteristic length scale that appears to be in good agreement with experimental observations. Moreover, the unsteadiness of the interface appears to be governed by both Kevin-Helmholtz and Rayleigh-Taylor instabilities. This dissertation also contains the first study of a projectile accelerating to reach the supercavitating state. Experimental results show that the transient development of the supercavity is governed by the formation of a vortex ring. Nuclei are shed from the forebody of the accelerating projectile and are entrained in the vortex ring core where they are subjected to low pressure and subsequently expand rapidly. A characteristic time scale for this supercavity development is presented. / Ph. D.

Severe accident studies have become important for understanding the environmental impact of nuclear power following the Three Mile Island (TMI) accident. Severe accident phenomena are interdisciplinary since they can include the interaction of molten corium with reactor structures and water, and the transport and release of fission products that carry vapors and aerosols. During an accident, molten corium may fall in the form of a jet into a water pool. The fragmentation of the corium jet is a critical process concerning Fuel-Coolant Interactions (FCI). A steam explosion could occur depending on jet fragmentation and dispersion in the water. A 2-D in-house CFD MATLAB script has been developed by employing the Volume of Fluid Method (VOF) to simulate jet fragmentation in a water pool. This research is the first study to use the Multidimensional Universal Limiter for Explicit Solution (MULES) algorithm to capture the interface behavior in the jet breakup process. The effect of the compression constant, the mesh sensitivity, and the face correction loop on the MULES are investigated in this thesis. Moreover, the effects of the jet inlet velocity and jet diameter on the jet breakup length are numerically studied using the newly developed code. The simulation results compared well with the experimental results and another numerical study found in the literature. / Master of Science / After the TMI accident, many countries have started experimental and numerical studies to investigate and predict the accident's possible outcomes. During a severe accident, the molten corium may drop into a water pool in the form of a jet. The jet contacts the water, fragments into droplets and disperses in the pool, which could then cause a steam explosion. A possible molten corium-water interaction is simulated using a 2-D in-house CFD code written in MATLAB in this study. Interface tracking is one of the most critical processes in multi-phase flow simulation, and the MULES algorithm is used to capture the interface in this study. It is the first study to use the MULES algorithm to investigate jet breakup behavior. The simulation results compared well with experimental data and other numerical studies.

The experiments on this project proceeded on the premise that adding an array of auxiliary jets behind a main jet injector would alleviate the large region of low pressure typically found downstream of a normal, sonic injector in supersonic flow and also possibly increase in intensity of the upstream high-pressure region. The secondary jet would, in theory, "push" the primary jet further into the flow, increasing the size of the obstacle as seen by the flow. The resulting increased high pressure upstream of the flow would increase the force on the body. Also, the presence of secondary jets would reduce the intensity of the primary jet's low-pressure region. These results would be beneficial to increase the force and decrease the nose-down moment associated with sonic, normal injection into a supersonic crossflow. Therefore, in application to hypersonic, high-altitude missile maneuvering, the firing of a thruster with such an array would result in both added force and a reduction of the moment usually associated with the pressure field on the missile. Such an array could allow the missile to perform purely translational maneuvers with less fuel, all the while keeping the target in view. To accomplish this task, some modern missiles use a second injector far downstream from the primary injector. This second injector's primary function is to negate the nose-down moment, and it adds little to the overall jet effectiveness. To this end, two sets of experiments were conducted: one with low jet pressure ratio, Poj/P1 = 13.65, and low Mach number of 2.4 with Po,inf = 3.74 atm and To,inf = 293K for proof of concept and one at primary conditions Poj/P1 = 620, M1 = 4, Po,inf = 10.21 atm, To,inf = 293K. Spark Shadowgraphs were taken at both of these cases to study the structures present in the flow field and to qualitatively assess the effects of the secondary jet injectors. Placed under the Mach disk of the main jet, the secondary jets are hypothesized to push the plume of the main jet further up into the flow, increasing the force on the plate, and Shadowgraphs were used to test this hypothesis. Schlieren pictures were taken at the high M1, high-pressure ratio test case to further study the interaction of the secondary jets with the main jet. Pressure Sensitive Paint, PSP, was used in both cases to gain a greater understanding of the surface pressure near the injectors for different jet configurations. It was discovered that the addition of secondary jets could indeed both increase the force generated by the main jet and reduce the undesirable nose-down moment created by the main jet. In the low M1, low pressure ratio conditions, the addition of one pair of jets manipulated the surface pressure such that the force on the plate increased by 17% and the nose-down moment was increased by 9% over the main jet only case. The further addition of one more pair of injectors increased the surface pressure force on the plate by 34% and increased the nose-down moment on the plate by 3% when compared to the Main Jet Only case. It is important to note that, these increases are due solely to the manipulation of the surface pressure force field and not the thrust of the secondary jets. The added thrust would increase the force on the plate and their position would insure an increase of a nose-up moment. One pair of secondary jets increases the injectant mass flow by about 2.3%. Therefore, the effects reported above are seen to be disproportionate to the amount of added injectant. For the primary test conditions (M1 = 4, Poj/P1 = 620, Po = 10.21 atm, To = 293K) the addition of two pairs of secondary jets had a force increase of 62% and a nose-down moment decrease of 38% over that of the main jet only case. Three pairs increased the force 71% and the decreased the nose-down moment by 26% and four pairs increased the force 91% but increased the nose-down moment by 33%. These values do not account for the thrust of the secondary jets. Accounting for the beneficial effects of the thrust of the secondary jets, the force on the plate for two pairs of secondary jets increased the force 70% and decreased the moment 42%. Three pairs increased the force 83% and decreased the moment 35%. The increase of force for four pairs of secondary jets was 106% and the increase in nose-down moment was only 21%. A point of diminishing returns was reached. As more pairs of injectors are added further and further from the main injector, the beneficial force effects are offset by a growing moment penalty. By considering the locations of the secondary injectors to the main injector for both the low Mach number, low-pressure ratio tests and the main tests conditions, it can be surmised that the greatest benefit from the secondary jets can be extracted when the jets are placed within the main injector's downstream low-pressure region. / Master of Science

Cette thèse porte sur l'étude de la diffraction avec le détecteur ATLAS au LHC. Après une brève introduction a la physique diffractive incluant la diffraction dure et molle, nous présenterons la production d'évènements "Jet-Gap-Jet" qui est particulirement intéressante pour tester les équations d'évolution de la Chromodynamique Quantique de Balitski Fadin Kuraev Lipatov. En utilisant des coupures permettant de sélectionner ce signal et une définition du "gap" basée sur la reconstruction des traces dans le détecteur interne d'ATLAS, nous observons un signal clair d'évènements "Jet-Gap-Jet" dans les données. A partir d'une taille de "demi-gap" de 0.8, les données ne peuvent pas être décrites de manière correcte en utilisant l'échantillon Monte Carlo des données de jets sans gap. Nous prouvons également que la production d'évènements "Jet-gap-Jet" avec les deux protons détectes dans AFP permet de réaliser un test propre de la théorie BFKL avec une luminosité de 300 pb-1. Dans la derniere partie de la these, nous presentons la production exclusive de jets et de pi+pi-. Apres la selection des donnes, le rapport signal sur bruit est de l'ordre de 5/9 (1/13) pour µ = 23 (46). Pour une luminosite integree respective de 40(300) fb-1 (pour un "pile-up" de 23(46)), cette mesure permettra d'etablir des contraintes sur les modeles theoriques dix fois plus precises qu'actuellement. La mesure de la production exclusive de pions en utilisant le detecteur ALFA permet de contraindre egalement les modeles exclusifs. Nous avons montre que les donnees accumulees par ALFA suffiront deja pour mesurer la section efficace de production et pour etudier differentes distributions comme la masse invariante du systeme pion-pion. / The thesis is devoted to the study of diffractive physics with the ATLAS detector at the LHC. After a short introduction to diffractive physics including soft and hard diffraction, we discuss Jet-Gap-Jet production at the LHC which is particularly interesting for testing the Balitski Fadin Kuraev Lipatov QCD evolution equation. Using the signal selection requirements and a gap definition based on tracks reconstructed in the ATLAS Inner Detector, we observe a clear signal of Jet-Gap-Jet events in the data. Starting from the half-gap size of 0.8 the data cannot be properly described using only the Jet Monte Carlo sample without gaps. Furthermore, we demonstrated that DPE JGJ production, with both protons tagged in the AFP stations, should provide a significant test of the BFKL theory, once the 300 pb−1 of integrated luminosity is collected. In the last part of the thesis, we discussed the processes of Central Exclusive Jet and Exclusive π+π− production. After the data selection, the signal to background ratio is found to be of about 5/9 (1/13) for < μ >= 23 (46). For a collected integrated luminosity of 40(300) fb−1 (for pile-up of 23(46)) this measurement will deliver ten times better constraints on the theoretical models than the most recent ones. The additional measurement of exclusive pion production, relying on the use of the ALFA stations, allows to constrain further the exclusive models. We demonstrated that a data sample collected by the ALFA detectors should be sufficient to measure the cross sectionand to study various distributions, especially the invariant mass of the pion-pion system.