Orientador: Osvaldir PecoraTaranto / Tese (doutorado) - Universidade Estadual de Campinas, Faculdade de Engenharia Quimica / Made available in DSpace on 2018-08-10T20:17:23Z (GMT). No. of bitstreams: 1 Parise_MariaRegina_D.pdf: 3017112 bytes, checksum: f14db15e7314590127e2a9a2ff621c9c (MD5) Previous issue date: 2007 / Resumo: A defluidização parcial ou total de partículas sólidas é um fenômeno indesejável em aplicações industriais envolvendo operações com leito fluidizado. Se as mudanças na fluidodinâmica do leito forem detectadas a tempo, pode-se evitar-la com o aumento da velocidade do gás de fluidização e/ou, em alguns casos, mediante a alteração da vazão de sólidos alimentados no sistema. A utilização de uma técnica que permita rapidamente identificar a região onde o leito está tendendo à defluidização é de suma importância, pois dessa maneira pode-se atuar no processo impedindo que haja perda de eficiência ou até mesmo a necessidade de parar a produção. Este trabalho teve como objetivo o desenvolvimento de uma metodologia capaz de identificar essa região em leito fluidizado gás-sólido, através de medidas de flutuação de pressão analisadas utilizando a transformada de Fourier juntamente com a Distribuição Exponencial Gaussiana. Para a verificação da metodologia proposta foram realizados ensaios experimentais utilizando areia e celulose microcristalina, alterando-se a altura do leito e o diâmetro médio das partículas. Os resultados mostraram que o método identifica claramente a região onde o leito está tendendo à defluidização, e tem grande potencial em aplicações industriais para o controle on line de processos em leito fluidizado gás-sólido. Além disso, a metodologia pode ser importante para detectar mudança de regime para a relação altura do leito e diâmetro da coluna de fluidização (H/D) superiores à unidade. Adicionalmente, foram realizados ensaios de secagem utilizando celulose microcristalina visando à possibilidade da identificação do ponto crítico (teor de umidade existente no final do período de taxa constante) utilizando as seguintes técnicas: metodologia proposta neste trabalho, freqüência dominante e desvio padrão da flutuação de pressão. Observou-se que para o sólido utilizado não foi possível detectar o ponto crítico através desses três tipos de análise. No entanto, a metodologia proposta pode ser utilizada na identificação do momento que a secagem não se encontra na fluidização requerida e está tendendo à defluidização / Abstract: The partial or complete bed defluidization is an undesired phenomenon in industrial application involving fluidized bed operations. If the changes in the hydrodynamic of the fluidized bed are detected early enough, it may be prevented by increasing the gas velocity and/or, in some cases, changing the solid feed in the system. The use of a technique that can quickly identify the region where the bed is tending to the defluidization is very important, because one can act in the process avoiding loss of efficiency or even the necessity of shutting down the process. This work was as objective the development a methodology capable of identifying this region in gas-solid fluidized bed, by pressure fluctuation measurements analyzed using Fourier Transform and exponential Gaussian distribution. In order to verify the methodology proposed, experimental tests were carried out using microcrystalline cellulose and sand, where the fixed bed height and particle mean diameter were varied. Results showed that the method clearly identifies the region where the bed is tending to the defluidization, and it has great potential on industrial applications to on line process control in gas-solid fluidized bed. Also, the methodology can be important to detect regime changes at bed aspect ratios (H/D) higher than unit. Additionally, experimental drying test were carried out using microcrystalline cellulose particles to verify the possibility of identification of the critical drying point (the moisture content related to the end of the constant rate period) by the following techniques: the methodology proposed in the present work, the dominant frequency and standard deviation of pressure fluctuations. It was observed that for the solid material used it was not possible to detect the critical drying point. However, the methodology proposed can be used on identification the moment that the drying is not in the desired fluidization regime and it is tending to defluidization / Doutorado / Engenharia de Processos / Doutor em Engenharia Química

An experimental investigation was performed to ascertain the nature of turbulence in a narrow apex angle isosceles triangular duct. The study involved the design and construction of a low noise, low turbulence wind tunnel that had an isosceles triangular test section with an apex angle of 11.5[degrees]. Experiments involved the measurement of velocity fluctuations using hot wire anemometry and wall pressure fluctuations using a condenser microphone. Measurement of the velocity fluctuations reconfirms the coexistence of laminar and turbulent regions at a given cross section for a range of Reynolds numbers. The laminar region is concentrated closer to the apex while the turbulent region is found closer to the base. The point of transition is a function of the Reynolds number and moves closer to the apex as the flow rate is increased. Moreover, it was found in this investigation that traditional scaling of the turbulent statistical quantities do not hold good in this geometry. Although velocity fluctuations showed distinctive flow regimes, no such distinction could be seen in the dynamic wall pressure data. The nature of the dynamic wall pressure was uniform throughout the entire cross section suggesting that wall pressure fluctuations, unlike the velocity fluctuations, are able to travel from the base to the apex, without being damped. This implies that the relationship between the velocity and the pressure fluctuations applicable in the other systems does not hold well in a narrow apex angle isosceles triangular duct. Further, the typical scaling relationships applied to wall pressure spectra of other geometries doesn't apply in this scenario and the ratio of the RMS pressure fluctuation to the mean shear is much higher compared to a flat plate or pipe flow situation.

Measurements have been performed to understand the sound source mechanism in turbulent boundary layer flow over two and three-dimensional surface discontinuities whose height is smaller than the incoming boundary layer thickness. The work was performed in two different types of boundary layers: a wall-jet flow and a conventional high Reynolds boundary layer. In the wall-jet flow, measurements of far field sound from two-dimensional forward facing steps, gaps with rounded corners and swept forward facing steps with rounded corners were made. The sound from a forward facing step is shown to exhibit effects of non-compactness. Rounding the step corner results in consistent drop in sound levels but the directivity of the sound field remains unchanged. The sound from gaps is dominated by the forward step component and remains unaffected by rounding of the backward step portion. The sound from swept forward facing steps was found to approximately obey an acoustic sweep independence principle up to a sweep angle of 30 deg when the spanwise inhomogeneity in the flow is accounted for using a simple source distribution model. Sweep independence is also observed for steps with corner rounding radii up to 25% of the step height. The work performed in the high Reynolds number boundary layer included measurements on forward facing steps with rounded corners and a three-dimensional circular embossment with the same height as the forward step. The highest Reynolds number based on discontinuity height achieved in this work was approximately 93,000. The results show that rounding the forward step corner has the same qualitative effect on far field sound as in the wall-jet boundary layer. Quantitatively, for similar boundary layer edge velocity the sound is higher than in the wall-jet flow. The near field measurements show that the separation bubble downstream of the step shrinks as the step corner is rounded while the bubble upstream remains unaffected by it. The unsteady surface force in the lower half of the vertical face of the step was found to be independent of corner rounding. The force on the downstream surface shows similar character within the separation bubble for each rounding but decays faster with increasing downstream distance due to reduced bubble size. The unsteady force measurements were applied to the theory of Glegg et al. (2014) and the resultant of the unsteady forces on the vertical face and downstream surface placed at the top corner of the step is shown to qualitatively describe the far field sound. The acoustic sweep independence principle was applied to the far field sound from the circular embossment and it has been shown that the sound from the three-dimensional geometry can be predicted with reasonable accuracy using sound from a two-dimensional forward step with the same span. / Ph. D.

RESUME : Les machines axiales à rotors contrarotatifs subsoniques sont une bonne solution pour les industries où de fortes élévations de pressions et d'efficacités sont nécessaires sans augmenter le diamètre ou la vitesse de rotation des rotors. Néanmoins, le comportement des CRS et les paramètres impactant ses performances ne sont pas encore totalement compris. Cette thèse mène une investigation expérimentale sur la performance et les paramètres influents sur un étage contrarotatif. La technique de design et les méthodes de mesure sont repris sur une thèse précédente réalisée au laboratoire Dynfluid (Arts et métiers ParisTech). Trois étages contrarotatifs ont été fabriqués (JW1, JW2 et JW3) et testés sur le banc d'essai normalisé AERO2FANS. Ces machines ont été conçues pour avoir le même point de fonctionnement mais avec une répartition de charge différente. Les résultats expérimentaux se concentrent dans un premier temps sur JW1. Les grandeurs physiques regardées sont l'efficacité globale et l'élévation de pression statique pour juger de la performance globale de la machine. La fluctuation de pression pariétale et le champ de vitesse sont aussi mesurés. L'impact du changement de rapport de vitesse ou la distance entre les deux rotors sur la machine JW1 a été étudiée grâce aux grandeurs physiques décrits précédemment. Enfin dans une dernière partie, les trois machines sont comparées toujours grâce aux grandeurs physiques définies précédemment. / ABSTRACT : The counter rotating subsonic axial flow fans could be a good solution for applications where the highly improved static pressure and efficiency are required without the increase of rotational speed and fan diameter. However, the mechanisms of high performance CRS and parameters influences are not well understood nowadays. This thesis is an experimental investigation of the performance and parameter studies of two counter rotatingaxial flow ducted fans. The design and measurement methods are based on the previous research work in Laboratory Dynfluid (Arts et Métiers ParisTech). Three Counter Rotating Stages (CRS) (named JW1, JW2 and JW3) are developed and tested on a normalized test bench (AERO2FANS). These systems have same design point and differ by the distribution of loading as well as the ratio of angular velocity between the Front Rotor (FR) and Rear Rotor (RR). The first part of results focus on the JW1. The overall performance is obtained by the experimental results of the static pressure rise and static efficiency, as well as the wall pressure fluctuations recorded by a microphone on the casing wall. The parameter study is conducted to investigate the effects of the axial distance and the ratio of angular velocity between the FR and RR on the global performance and flow fields measured by Laser Doppler Velocimetry (LDV).The last part of the work is devoted to analyze the differences of the three CRS with different distribution of work, in terms of the global performance and flow features.

L'écoulement autour des véhicules produit une couche limite turbulente très proche de la paroi. Le caractère turbulent induit des fluctuations de pression pariétale qui font vibrer les panneaux du véhicule. Ces vibrations sont alors transmises à travers la structure et rayonnent du bruit dans l’habitacle. Les niveaux sonores dus à l'écoulement augmentent avec la vitesse du véhicule. Pour cette raison, cette problématique connaît un intérêt croissant dans le secteur aéronautique.Le but de cette thèse est double : comprendre les mécanismes à l’origine de ces fluctuations de pression à la paroi et prédire l’excitation de la structure avion due à l’écoulement turbulent.Pour ce faire, des calculs Large Eddy Simulation (LES) sont disponibles. Il s’agit de bases de données numériques d’écoulements de couches limites turbulentes en présence de gradients de pression favorable, adverse et nul. Ceci permet de caractériser l’écoulement sur des géométries courbes telles que la pointe avant d’un avion. L’effet du gradient de pression sur des structures cohérentes de type « hairpins » et paquets de « hairpins » a pu être identifié et quantifié à travers des méthodes de visualisation et d’analyse statistique. Une méthode d’estimation stochastique du champ de vitesse a révélé la présence de tourbillons contra-rotatifs au-dessus des paquets de hairpins. Ces tourbillons ont une vorticité opposée à celle des hairpins et un modèle de « hairpins inversé » a été proposé.En s’inspirant du travail de Ahn et al. (2010), un modèle stochastique de spectre de la pression pariétale a été développé. Il s’agit de reconstruire un champ stochastique de vitesse instantanée et d’en déduire le champ de pression à la paroi en résolvant une équation de Poisson sur la pression. Le champ de vitesse est obtenu en soumettant des structures de type paquets de hairpins à un écoulement moyen. Les caractéristiques des paquets de hairpins en fonction du gradient de pression sont basées sur l’analyse des bases LES. Les résultats de ce modèle sont comparés à ceux issues de bases de données numériques et expérimentales. Enfin, ce modèle est utilisé pour caractériser l’écoulement de couche limite turbulente dans une simulation de Statistical Energy Analysis (SEA) afin de prédire les niveaux de vibration des panneaux d’une portion de fuselage d’avion. / The flow around vehicles creates a turbulent boundary layer in the vicinity of the wall. The turbulent behavior induces pressure fluctuations that make the panels vibrate. These vibrations are then transmitted though the structure of the vehicle and radiate noise inside the cabin. The flow-induced noise levels increase with the speed of the vehicle. For this reason, aircraft manufacturers show a great interest in this topic.There are two objectives for this thesis: understand the mechanisms responsible for the wall-pressure fluctuations and predict this source of aircraft panel excitation.A study of available Large Eddy Simulation (LES) computations was performed. The database consists in simulations of turbulent boundary layer flows submitted to favorable, adverse and zero pressure gradients. This is necessary to understand the nature of the flow over curved geometries such as the aircraft flight deck. The effect of pressure gradients on coherent hairpin structures and hairpin packets could be identified and quantified based on visualization and statistical analysis methods. Linear stochastic estimation of the velocity fields revealed a pair of counter-rotating streamwise vortices above hairpin packets. These vortices have a vorticity opposite to that of the hairpins and an “inverse hairpin” model was proposed.Following the work of Ahn et al. (2010), a stochastic model for wall-pressure spectrum was developed. The idea is to build a stochastic turbulent velocity field using hairpin packets which are subjected to a mean flow. The characteristics of the packets depending on the pressure gradient are based on the analyses of the LES database. The pressure field at the wall is obtained by solving a Poisson equation. The results of the hairpin packet model are compared to numerical and experimental data. Finally, the model is used as input for a Statistical Energy Analysis (SEA) simulation in order to predict the levels of vibrations of panels submitted to a turbulent boundary layer flow over a portion of an aircraft cabin.

Les vibrations induites par l'écoulement dans le coeur du REP peuvent provoquer une usure par frottement des crayons combustibles par friction au niveau des contacts entre la cellule de grille et les crayons des assemblages combustibles. Cela peut entraîner des dommages irréversibles de la gaine du crayon combustible et compromettre la première barrière de sûreté du réacteur. Assurer l'intégrité de la gaine est une préoccupation majeure dans la sûreté du réacteur. Cependant, les spectres d'excitation des forces fluides agissant sur les crayons ne sont pas bien connus. Le but de cette thèse est d'utiliser des éléments géométriques simples pour reproduire des cellules de grilles d'un REP. SGE ont été effectuées sur une conduite annulaire avec différents maillages en utilisant le code TrioCFD. Une étude de sensibilité de maillage a été réalisée afin de proposer un maillage reproduisant correctement les résultats dans la littérature. Ces informations de résolution de maillage ont été utilisées lors de la réalisation des simulations en utilisant divers obstacles géométriques intérieurs à la conduite, i.e., des ailettes de mélange, une grille circulaire et une combinaison de grille carrée et d'ailettes de mélange. Un maillage hybride a été utilisé dans le cas des ailettes de mélange et dans le cas de cellule de grille carrée. Les caractéristiques hydrauliques ainsi que la pression pariétale ont été analysées dans chaque cas. Il apparaît que la grille carrée est une combinaison approximative du cas des ailettes de mélange et du cas de la grille circulaire. Les simulations ont été comparés avec des mesures réalisées au CEA / Flow-induced vibrations in the pressurized water reactor core can cause fretting wear in the fuel rods. Due to friction, wear occurs at the contact locations between the spacer grid and the fuel rod. This may compromise the first safety barrier of the nuclear reactor by damaging the fuel rod cladding. In order to ensure the integrity of the cladding, it is necessary to know the random fluctuating forces acting on the rods. However, the spectra for these fluid forces are not well known. The goal of this thesis is to use simple geometrical elements to check the reproducibility of realistic PWR spacer grids. As a first step, LES were performed on annular pipe for different mesh refinements using the CFD code TrioCFD. A mesh sensitivity study was performed to propose a good mesh for reproducing standard literature results. This information on mesh resolution was used when carrying out simulations using various geometric obstacles inside the pipe-mixing vanes, circular spacer grid and a combination of square spacer grid with mixing vanes. Structured mesh was generated for the annular pipe case and circular grid case. An innovative hybrid mesh was used for the two remaining cases of the mixing vanes and the square grid; keeping unstructured mesh around the obstacles and structured mesh in the rest of the domain. Both hydraulic and wall pressure characteristics were analyzed for each case. The results for the square grid case were found to be an approximate combination of the mixing vane case and circular grid case. Simulation results were compared with experiments performed at CEA Cadarache. Some preliminary comparisons were also made with classical empirical models.

Bio-fuels, being the primary alternative to the fossil fuels, used in the internal combustion engines are subjected to constant development. The development of alternative Ethanol Diesel (ED95) formulations at AVL Motortestcenter AB has demanded a test facility capable of evaluating the combustion quality of these specimens. A test cell capable of evaluating fuels operating on the compression ignition concept was required for this reason. The aim of this thesis is to develop a high pressure fuel delivery system for a single cylinder test cell engine. The literature review conducted offered knowledge on stages involved in the development of the fuel and the operation of high pressure fuel systems for engines operating on the Diesel concept. Knowledge was acquired on phenomenon such as pressure fluctuations and information regarding engine test cells was familiarised. Scania's XPI fuel system being the designated fuel system for the test cell was studied and adaptations required for its implementation in the single cylinder test cell was investigated. Based on the information acquired, recommendations for the set up of the high pressure fuel system for the single cylinder test cell engine are mentioned. / Förnyelsebara biobränslen är det primära alternativet till fossila bränslen för användning i interna förbränningsmotorer och är under ständig utveckling. För den fortsatta utvecklingen av etanoldiesel (ED95) genom provning av nya formuleringar vid AVL Motortestcenter AB krävs ett lämplig testupplägg. Förbränningskvalitetsutvärderingen kräver en avancerad testcell där bränslets förbränningsegenskaper kan utvärderas. Målet med detta arbete var att utveckla ett högtrycksbränslesystem lämpligt för en singelcylindrig forskningsmotor som arbetar enligt kompressionständningsprincipen (dieselprincipen). Litteraturstudien samlade kunskap om bränsleutveckling samt kunskap om dieselmotorers högtrycksbränslesystemen, dess uppbyggnad och utmaningar. Kunskap om fenomen som tryckoscillationer och kavitation i bränslesystem samt förståelse för motorprovcellers uppbyggnad införskaffades. Scanias XPI bränslesystem, som forskningsmotorns högtrycks- bränslesystem ska efterlikna, studerades och adaptioner för att passa till encylinderkörningar i provcell utvärderades. Baserat på informationen ges rekommendationer på hur Scanias XPI system kan implementeras och justeras för att fungera i AVL’s singelcylinderprovcell.

No description available.

Le bruit généré par la détente d'un écoulement sous pression à travers des plaques multi-perforées ou des diaphragmes est étudié expérimentalement. Cette analyse est menée sur deux configurations géométriques distinctes dans lesquelles la plaque perforée est placée à la sortie d'un conduit cylindrique (configuration de jet libre) ou à l'intérieur de celui-ci (configuration de jet confiné).Dans un premier temps, une étude paramétrique acoustique est effectuée pour ces deux configurations en variant les caractéristiques géométriques des plaques perforées et les points de fonctionnement dans des régimes subsoniques et supersoniques. Les différentes sources de rayonnement pouvant apparaitre sur de tels systèmes de détente, sont alors identifiées. Par ailleurs, les effets acoustiques de chacun des paramètres géométriques sont mis en lumière, offrant ainsi une aide à la conception silencieuse de tels systèmes. Dans un second temps, l'intérêt est porté sur l'analyse de la composante à large bande dominante: le bruit de mélange. Cette étude est menée sur la configuration de jet libre et s'appuie sur des visualisations strioscopiques ainsi que sur des mesures de vélocimétrie par image de particules couplées à des acquisitions acoustiques en champ lointain. Dans le cas des diaphragmes, les différents résultats mettent en évidence des mécanismes sources du bruit de mélange similaires à ceux observés dans la littérature pour les jets isolés issus de tuyères. Le rayonnement à l'aval, dominant, est généré par l'interaction de grosses structures turbulentes cohérentes à la fin du cône potentiel du jet, tandis que dans les autres directions, le bruit est généré par la turbulence de petite échelle dans les couches de cisaillement du jet.Pour les plaques multi-perforées, des mécanismes comparables sont également identifiés. Néanmoins, selon la géométrie de ces plaques, deux zones sources distinctes du rayonnement aval sont identifiées favorisant l'apparition de deux bosses dans les spectres en champ lointain. Dans le cas de perforations éloignées, la bosse à plus haute fréquence domine le spectre aval et l'interaction des grosses structures turbulentes se produit au niveau de la fin du cône potentiel des jets. Lorsque les perforations sont en revanche proches, c'est la bosse à basse fréquence qui domine et l'interaction des grosses structures turbulentes cohérentes semble se produire près de la fin du cône potentiel du gros jet équivalent formé à l'aval à partir du mélange de l'ensemble des jets issus des perforations. Dans les autres directions, l'espacement des perforations joue également un rôle important sur le rayonnement acoustique, du fait d'une interaction plus ou moins rapide des jets entre eux. Cela a alors pour effet de modifier les zones de cisaillement et en conséquence le rayonnement acoustique de la même manière que dans la direction aval. / The noise generated by the expansion of a pressurized flow through multi-perforated plates or diaphragms is experimentally investigated. The analysis is conducted on two distinct geometrical configurations in which the perforated plate is placed at the outlet of (free jet configuration) or inside (ducted jet configuration) a cylindrical duct.Firstly, an acoustic parametric study is carried out on these two configurations for various perforated plate geometries and for a number of operating points ranging from subsonic to supersonic. The different acoustic sources that can arise from such systems are thus identified. Furthermore, the effect of each geometrical parameter onto the radiated sound field is highlighted, thus providing guidelines for the silent design of such pressure release devices.In a second step, the focus is on the dominant broadband component, that is, the mixing noise. This part of the study is dedicated to the free jet configuration and is based on Schlieren imaging, as well as on Particle Image Velocimetry measurements, both coupled far-field sound measurements.In the diaphragm cases, the aerodynamic results show that the source mechanisms are similar to those reported in the literature about isolated jets from conventional nozzles. The downstream radiation is generated by the interaction of large coherent structures at the end of the jet potential core, while in the other directions it is generated by the small-scale turbulence from the shear layer.For multi-perforated plates, comparable mechanisms are also observed. However, depending on the plate geometry, two distinct source regions contributing to the downstream radiation are identified. They explain the presence of two broadband humps in the far-field spectra. In the case of widely spaced perforations, the higher frequency hump in the downstream spectrum increases and the interaction of the large turbulent structures occurs mainly at the end of the potential core of the small jets issuing the perforations. Conversely, when these perforations are close to each other, the small jets rapidly merge into a single larger one that has a longer potential core. As a result, larger coherent structures interact downstream of the small jet mixing region and therefore, a low-frequency hump dominates the downstream spectrum. In the other directions, the perforation spacing has also a significant impact on the acoustic radiation, due to a more or less rapid interaction of the jets. Consequently, the turbulence, as well as the shear zones of the various mixing layers, are modified. The geometric parameters thus have similar effects on the cross-stream as on the downstream radiation.