Orientadores: José Roberto de França Arruda, Pierrick Lotton, Guillaume Penelet / Tese (doutorado) - Universidade Estadual de Campinas, Faculdade de Engenharia Mecânica / Made available in DSpace on 2018-08-24T19:14:04Z (GMT). No. of bitstreams: 1 Bannwart_FlaviodeCampos_D.pdf: 33288736 bytes, checksum: 8166e34982ed775a474e0817a4157baf (MD5) Previous issue date: 2014 / Resumo: O projeto de um motor termoacústico (TA) se torna viabilizado à medida da con?abilidade de sua previsão de desempenho. Uma tentativa para o êxito nessa previsão vem do conhecimento da matriz de transferência do núcleo termoacústico (NTA), que pode ser explorada em modelos analíticos para o motor considerado. A matriz de transferência por si só pode ser obtida ou por modelagem analítica ou medições acústicas. As últimas, no entanto, consistem em uma opção interessante para se evitar considerações termo-físicas ou geométricas de estruturas complexas, uma vez que o NTA é tratado como uma caixa preta. No entanto, antes de se prosseguir com a abordagem experimental, uma solução analítica é apresentada, apenas para ?ns de comparação, mas que contempla somente os casos de materiais de geometria simples, tal como um catalisador de cerâmica, por exemplo. Em relação à abordagem experimental, três diferentes métodos são apresentados. Um método clássico de duas cargas é aplicado em duas con?gurações distintas e, além disso, um método alternativo com base em medições de impedância é aqui desenvolvido e aplicado. Uma comparação entre estas três abordagens é realizada por meio de uma avaliação de performance experimental e também por uma análise de sensibilidade, de modo a se conhecer as perspectivas de viabilidade de cada método. Quatro diferentes materiais são testados, cada um sendo usado como o elemento poroso colocado no interior do NTA, que é por sua vez submetido a diferentes regimes de gradiente de temperatura. Estes materiais são escolhidos de tal maneira a cobrir uma vasta gama de porosidades compreendidas entre esperados stack puro e regenerador puro. O método alternativo foi bem sucedido no seu objectivo para todos os materiais, ao contrário do método clássico de duas cargas. Desta forma, as matrizes de transferência medidas são aplicadas em uma modelagem dedicada a prever tanto a frequência operacional como o ganho de ampli?ca- ção TA intrínseca. Tais parâmetros são otimizados em simulações para dois modelos de motores TA básicos, um de onda estacionária e outro progressiva, variando-se parâmetros geométricos dos componentes anexos ao NTA. Uma análise comparativa mostra em que condições o limiar TA é esperado ou não para cada material, e também revela as limitações do aparato experimental no que se refere às dimensões adequadas para melhor se ajustarem às investigações de desempenho / Abstract: The design of a thermoacoustic (TA) engine is improved towards the reliability of its performance prediction. An attempt to succeed in this prediction comes from the knowledge of the TA core (TAC) transfer matrix, which can be exploited in analytical models for the given engine. The transfer (T) matrix itself may be obtained either by analytical modeling or acoustic measurements. The latter consist in an interesting option to avoid thermo-physical or geometrical considerations of complex structures, as the TAC is treated as a black box. However, before proceeding with the experimental approach, an analytical solution is presented for comparison purposes, but it contemplates only cases of materials of simple geometry such as a ceramic catalyst. Concerning the experimental approach, three different methods are put forward. A classical two-load method is applied in two different con?gurations and an alternative method based on impedance measurements is here developed and applied. A comparison between these approaches is evaluated by means of a sensitivity analysis, in order to investigate the feasibility of each method in further explorations. Four different materials are tested, each one playing the porous element allotted inside the TAC, which is in its turn submitted to several different regimes of steady state temperature gradient. These materials are chosen in such a way as to cover the wide range of porosities comprised between expected pure stack and pure regenerator. The alternative method succeeds on its purpose for all materials, contrarily to the classical two-load method. In this manner, the measured transfer matrices are applied into a proper modeling devoted to predict both the operating frequency and the intrinsic TA ampli?cation gain. Such parameters are optimized for two basic TA engine models, either standing or traveling-wave con?guration, by searching for the corresponding geometrical parameters of the TAC surrounding components. A comparative analysis shows in what conditions the TA threshold is expected or not for each material, but it also reveals the limitations of the experimental apparatus in what concerns the appropriate dimensions to better ?t the performance investigations / Doutorado / Mecanica dos Sólidos e Projeto Mecanico / Doutor em Engenharia Mecânica

Modern gas turbine designs often include lean premixed combustion for its emissions benefits; however, this type of combustion process is susceptible to self-excited combustion instabilities that can lead to damaging heat loads and system vibrations. This study focuses on identifying a mechanism of combustion instability of a reacting jet in cross flow, a flow feature that is widely used in the design of gas turbine combustion systems. Experimental results from a related study are used to validate and complement three numerical tools that are applied in this study – self-excited Large Eddy Simulations, 3D thermoacoustic modeling, and 1D instability modeling. Based on the experimental and numerical results, a mechanism was identified that included a contribution from the jet in cross flow impedance as well as an overall jet flame time lag. The jet impedance is simply a function of the acoustic properties of the geometry while the flame time lag can be separated into jet velocity, equivalence ratio, and strain fluctuations, depending on the operating conditions and setup. For the specific application investigated in this study, it was found that the jet velocity and equivalence ratio fluctuations are important, however, the effect of the strain fluctuations on the heat release are minimal due to the high operating pressure. A mathematical heat release model was derived based on the proposed mechanism and implemented into a 3D thermoacoustic tool as well as a 1D instability tool. A three-point stability trend observed in the experimental data was correctly captured by the 3D thermoacoustic tool using the derived heat release model. Stability maps were generated with the 1D instability tool to demonstrate regions of stable operation that can be achieved as a function of the proposed mechanism parameters. The relative effect of the reacting jet in cross flow on the two dominant unstable modes was correctly captured in the stability maps. While additional mechanisms for a reacting jet in cross flow are possible at differing flow conditions, the mechanism proposed in this study was shown to correctly replicate the stability trends observed in the experimental tests and provides a fundamental understanding that can be applied for combustion system design.

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Yes / Thermoacoustic refrigeration is an evolving cooling technology in which the acoustic power is used to pump heat. The operating conditions and geometric parameters are important for the thermoacoustic refrigerator performance, as they affect both its performance and the temperature difference across the stack. This paper investigates the effect of the stack geometric parameters and operating conditions on the performance of a standing wave thermoacoustic refrigerator and the temperature difference across the stack. DeltaEC software is used to make the thermoacoustic refrigerator model. From the obtained results, normalised values for the operating conditions andgeometric parameters are collected to compromise both the performance and the temperature difference across the stack.

Les instabilités thermoacoustiques, également appelées instabilités de combustion, sont un problème majeur pour la production d’électricité ainsi que dans l’industrie aérospatiale. Ces instabilités sont dues à un transfert d’énergie entre une source chaude, le plus souvent une flamme stabilisée dans un brûleur, et le champ acoustique environnant. Les instabilités de combustion peuvent avoir de nombreuses conséquences délétères telles que l’extinction de la flamme, l’augmentation des flux de chaleur pariétaux, l’émission d’ondes sonores de grande amplitude à certaines fréquences, des vibrations importantes, des dégâts structurels et même l’explosion du moteur dans certains cas. Étant donné les conséquences potentielles de tels phénomènes, d’importants moyens de recherche ont été consacrés à la prédiction de l’apparition d’instabilités de combustion dans les chaudières, les moteurs de fusée et les turbines à gaz ces dernières décennies. Néanmoins, le cadre théorique associé à l’étude de ces instabilités est complexe et nécessite l’emploi de nombreuses disciplines de la physique. De plus, les brûleurs industriels sont constitués de nombreuses cavités tridimensionnelles interagissant entre elles d’un point de vue acoustique. Pour toutes ces raisons, la prédiction de la stabilité thermoacoustique d’un brûleur demeure une tâche ardue à ce jour... (Voir le texte de la thèse pour la suite du résumé) / Thermoacoustic instabilities, also known as combustion instabilities, are a major concern in the aerospace and energy production industries. They are due to an energy transfer that occurs between a heat source, usually a flame stabilized inside a combustor, and the surrounding acoustic field and may lead to undesirable phenomena such as flame extinction, increased heat fluxes, very large sound emissions at certain frequencies, vibration, structural damage and even catastrophic failure in some cases. Given the potential consequences of such phenomena, a large research effort has been devoted to predicting the onset of combustion instabilities in modern boilers, rocket engines and gas turbines during the past few decades. Unfortunately, the theoretical framework associated with the study of thermoacoustic instabilities is complex and multi-physics and the geometry of practical combustors is an intricate arrangement of 3D cavities. As a consequence, predicting the thermoacoustic stability of a combustor at an early design stage is a challenging task to date... (See inside the manuscript for the remainder of the abstract)

<div>Enhancements of gas turbine engines efficiency are critical for the development of the next generation of clean and efficient aircraft. With the increase in combustion temperatures, cooling of the turbine blades poses one of the most important thermal management issues. The current and most adopted solution is to flow cooling air bled from the compressor through channels inside turbine blades. Fuel preheating, meant to increase combustion efficiency, could be used to cool such air flow in fuel-air heat exchangers. However, when fuel thermodynamic states approach supercritical pressures and temperatures, large amplitude oscillations have been known to occur with catastrophic hardware failures. For this reason, the use of supercritical fuels in fuel-air heat exchangers has been avoided, thereby reducing the fuel's cooling potential and the overall efficiency of the aircraft. Engine manufacturers desire a model capable of predicting the onset of such disruptive thermoacoustic oscillations. To this goal, we study theoretically and numerically transcritical thermoacoustic oscillations, i.e., thermoacoustic instabilities manifesting themselves when a fluid is heated close to its critical point, where abrupt changes of thermodynamic properties appear. Details of this work will be on the development of a transcritical thermoacoustic theory and on numerical results from linear stability analysis and high-fidelity Navier-Stokes simulations. Meeting the needs of industry and with the intent of pushing technological and scientific barriers, we propose to exploit such powerful oscillations for energy conversion through the use of the first-ever-built transcritical thermoacoustic engine.</div>

<p>Proton beam therapy has shown great promise for cancer treatment due to its high precision in irradiating tumor volumes. However, due to the massive size and expense of the cyclotrons/synchrotrons needed to accelerate the protons, the widespread use of proton therapy is limited. Laser plasma accelerated (LPA) proton beams may be a potential alternative to conventional proton beams: by shooting an ultraintense, ultrashort pulsed laser at a thin target, a plasma sheath electric field may be formed with the capability of accelerating protons to potentially therapeutic energies in very short distances. In addition to accessibility, there is significant uncertainty in proton range in heterogeneous tissues. Thermoacoustic computed tomographic (TACT) imaging has the potential to provide <em>in vivo</em> dose imaging and range verification to address these uncertainties. TACT measures thermoacoustic waves generated from the absorbed dose and implements a 3D filtered backprojection to reconstruct volumetric images of the dose. The purpose of this thesis is to determine the feasibility of integrating LPA proton beams with thermoacoustic imaging into a novel image-guided small animal therapy platform as an early step towards clinical  translation to address the issues of accessibility and dosimetric spatial uncertainty. A Monte Carlo (MC) method is used to simulate an LPA proton beam with characteristics based on literature, thermoacoustic waves are simulated on a voxel-wise basis of the MC dose, and 3D filtered backprojection is used to reconstruct a volumetric image of the dose. In Specific Aim 1, the dependence of image accuracy on transducer array angular coverage is investigated; in Specific Aim 2, an iterative reconstruction algorithm is implemented to improve image accuracy through increased sampling of projection space when transducer array angular coverage is insufficient; and in Specific Aim 3, the detector sensitivity to dose is determined for several therapeutic endpoints. The work presented in this thesis not only demonstrates the feasibility of integrating LPA and thermoacoustic technologies but necessary design changes to realize a functional small animal platform.</p>

Finite amplitude perturbations in compressible media are ubiquitous in scientific and engineering applications such as gas-turbine engines, rocket propulsion systems, combustion instabilities, inhomogeneous solids, and traffic flow prediction models, to name a few. Small amplitude waves in compressible fluids propagate as sound and are very well described by linear theory. On the other hand, the theory of nonlinear acoustics, concerning high-amplitude wave propagation (Mach<2) is relatively underdeveloped. Most of the theoretical development in nonlinear acoustics has focused on wave steepening and has been centered around the Burgers' equation, which can be extended to nonlinear acoustics only for purely one-way traveling waves. In this dissertation, theoretical and computational developments are discussed with the objective of advancing the multi-fidelity modeling of nonlinear acoustics, ranging from quasi one-dimensional high-amplitude waves to combustion-induced detonation waves. <br> <br> We begin with the theoretical study of spectral energy cascade due to the propagation of high amplitude sound in the absence of thermal sources. To this end, a first-principles-based system of governing equations, correct up to second order in perturbation variables is derived. The exact energy corollary of such second-order system of equations is then formulated and used to elucidate the spectral energy dynamics of nonlinear acoustic waves. We then extend this analysis to thermoacoustically unstable waves -- i.e. amplified as a result of thermoacoustic instability. We drive such instability up until the generation of shock waves. We further study the nonlinear wave propagation in geometrically complex case of waves induced by the spark plasma between the electrodes. This case adds the geometrical complexity of a curved, three-dimensional shock, yielding vorticity production due to baroclinic torque. Finally, detonation waves are simulated by using a low-order approach, in a periodic setup subjected to high pressure inlet and exhaust of combustible gaseous mixture. An order adaptive fully compressible and unstructured Navier Stokes solver is currently under development to enable higher fidelity studies of both the spark plasma and detonation wave problem in the future. <br>

This thesis describes an experimental investigation of the response of lean turbulent swirling flames with different degrees of premixedness (i.e. different mixture patterns) to acoustic forcing using the same burner configuration and varying only the fuel injection strategy. Special emphasis was placed on the amplitude dependence of their response. Also, the behaviour of self-excited fully premixed flames was examined. kHz OH* chemiluminescence was used to study qualitatively the heat release response of the flames, while kHz OH Planar Laser Induced Fluorescence (PLIF) was employed to understand the response of the flame structure and the behaviour of the various parts of the flame. The Proper Orthogonal Decomposition (POD) method was used to extract the dominant structures of the flame and their periodicity. In the first part of the thesis, self-excited oscillations were induced by extending the length of the duct downstream of the bluff body. It was found that the longer the duct length and the higher the equivalence ratio, the stronger the self-excited oscillations were, with the effect of duct length being much stronger. The dominant frequencies of the system were found to increase with equivalence ratio and bulk velocity and decrease with duct length. For some conditions, three simultaneous periodic motions were observed, where the third motion oscillated at a frequency equal to the difference of the other two frequencies. A novel application of the POD method was proposed to estimate the convection velocity from the most dominant reaction zone structures detected by OH* chemiluminescence imaging. For a range of conditions, the convection velocity was found to be in the range of 1.4-1.7 bulk flow velocities at the inlet of the combustor. In the second part, the response of fully premixed, non-premixed with radial fuel injection (NPR) and axial fuel injection (NPA) flames was investigated and compared. All systems exhibited a nonlinear response to acoustic forcing. The highest response was observed by the NPR flame, followed by the fully premixed and the non-premixed with axial fuel injection flame. The proximity of forced flames to blow-off was found to be critical in their heat release response, as close to blow-off the flame response was significantly lower than that farther from blow-off. In the NPR and NPA systems, it was shown that the acoustic forcing reduced the stability of the flame and the stability decreased with the increase in forcing amplitude. In the fully premixed system, the flame area modulations constituted an important mechanism of the system, while in the NPR system both flame area and equivalence ratio modulations were important mechanisms of the heat release modulations. The quantification of the local response of the various parts of the flame at the forcing frequency showed that the ratio RL (OH fluctuation at 160 Hz to the total variance of OH) was greater in the inner shear layer region than in the other parts in the case of NPR and NPA flames. In fully premixed flames, greater RL values were observed in large regions on the downstream side of the flame than those in the ISL region close to the bluff body. The ratio of the convection velocity to the bulk velocity was estimated to be 0.54 for the NPR flame, while it was found to be unity for the respective fully premixed flame. In the last part of the thesis, the response of ethanol spray flames to acoustic oscillations was investigated. The nonlinear response was very low, which was reduced closer to blow-off. The ratio RL was the highest in the spray outer cone region, downstream of the annular air passage, while RL values were very low in the inner cone region, downstream of the bluff body. Unlike NPR and fully premixed flames, in case of spray and NPA systems, it was found that forcing did not affect greatly the flame structure. The understanding of the nonlinear response of flames with different degrees of premixedness in a configuration relevant to industrial systems contributes to the development of reliable flame response models and lean-burn devices, because the degree of premixedness affects greatly the flame response. Also, the understanding of the behaviour of forced spray flames is of great interest for industrial applications, contributing to the development of thermoacoustic models for liquid fuelled combustors. Finally, the estimation of the convection velocity is of importance in the modelling of self-excited flames and flame response models, since the convection velocity affects the flame response significantly.