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The work presented here discusses the effects of strong acoustic forcing on jet flames in crossflow (JFICF) and the physical mechanisms behind theses effects. For forced non-premixed JFICF, the jet fuel flow is modulated using an acoustic speaker system, which results in a drastic decrease in flame length and soot luminosity. Forced JFICF are characterized by periodic ejections of high-momentum, deeply penetrating vortical structures, which draws air into the jet nozzle and enhances mixing in the nearfield region of the jet. Mixture fraction images of the non-reacting forced jet in crossflow are obtained from acetone planar laser-induced fluorescence and show that the ejected jet fluid is effectively partially premixed. Flame luminosity images and exhaust gas measurements show that forced non-premixed JFICF exhibit similar characteristics to unforced partially-premixed JFICF. Both strong forcing and air dilution result in net reductions in NOx, but increases in CO and unburned hydrocarbons. NOx scaling analysis is presented for both forced non-premixed and unforced partially-premixed flames. Using flame volume arguments, EINOx scales with amplitude ratio for forced non- premixed flames, but does not scale with air dilution for unforced partially-premixed flames. The difference in scaling behavior is attributed to differences in flame structure. The effect of forcing on the flowfield dynamics of non-premixed JFICF is investigated using high-speed stereoscopic particle image velocimetry and luminosity imaging. The frequency spectra of the windward and lee-side flame base motions obtained from luminosity movies of the forced JFICF show a peak at the forcing frequency in the lee-side spectrum, but not on the windward-side spectrum. The lee-side flame base responds to the forcing frequency because the lee-side flame base stabilizes closer to the jet exit. The windward-side flame base does not respond to the forcing frequency because the integrated effect of the incident crossflow and vortical ejections leads to extinction of the flame base. From the PIV measurements, flowfield statistics are conditioned at the flame base. The local gas velocity at the flame base did not collapse for forced and unforced JFICF and was found to exceed 3SL. The flame propagation velocity was determined from the motion of the flame base, which is inferred from regions of evaporated seed particles in the time-resolved PIV images. The flame propagation velocity collapses for forced and unforced JFICF, which implies that the flame base is an edge flame; however, the most probable propagation velocity, approximately 2-3SL, is larger than propagation velocity predicted by edge flame theories. A possible explanation is that the flame propagation is enhanced by turbulent intensities and flame curvature. / text

The contributions of vortex stretching, dilatation, baroclinic torque, and viscous diffusion to vorticity transport are experimentally investigated in a high-Reynolds number cavity combustor using high-speed particle image velocimetry and broadband chemiluminescence. An adaptive wall geometry forming converging, diverging, and nominal configurations is implemented to study the effects of pressure gradient on local flow physics and vorticity dynamics. The spatial profiles of the local turbulence terms are conditioned on the mean flame front to characterize the influence of the pressure gradient field and exothermic heat release on vortex dynamics in the cavity. In addition to isolate the influence of combustion on the flow, a nonreacting analysis is performed and a correlation is made between combustor geometry and the turbulence transport processes. Vorticity transport through dilatation was found to be significant relative to the other transport terms across all the configurations studied. These results contrast with direct numerical simulations of high Reynolds number flows in homogeneous isentropic turbulence. In addition, a scaling is proposed to quantify the significance of the flow induced vorticity and pressure fields on dilatation and baroclinic torque vorticity production. Experimental studies of similar confined combustors show a similar trend to the numerical studies with baroclinic torque dominating the transport mechanisms, motivating this study to understand the dependence of vorticity transport on the underlying flow physics.

A compreensão dos mecanismos de estabilidade de chamas é de extrema importância tanto para o projeto/dimensionamento de queimadores utilizados em fornos e fornalhas industriais, câmaras de combustão de turbinas a gás e flares; como para a substituição de combustíveis em queimadores existentes. Há um intervalo de condições (como velocidade de descarga do jato e concentração de combustível na mistura gasosa) na qual a combustão estável pode ser mantida, sendo limitada por dois fenômenos denominados como liftoff (descolamento da base da chama do bocal e posterior estabilização desta a certa distância do bocal) e blowout (desprendimento e extinção da chama). Por razões de segurança, operações próximas às condições em que o blowout pode ocorrer devem ser evitadas. Muitas teorias têm sido publicadas para descrever as características de liftoff e blowout de chamas de difusão turbulenta. Este trabalho apresenta algumas destas teorias, bem como as hipóteses assumidas e os processos físicos considerados responsáveis por estes fenômenos (liftoff e blowout). Correlações para a previsão da velocidade de blowout e resultados experimentais disponíveis na literatura também são apresentados. Uma nova correlação para a velocidade de blowout é proposta, a qual se baseia nos movimentos de grande escala observados em jatos turbulentos e no adimensional número de Damköhler (relação entre o tempo de cinética química e o tempo de mistura dos reagentes e destes com os produtos da reação). Comparações entre as previsões da correlação proposta com resultados experimentais e com previsões de outras correlações disponíveis na literatura foram realizadas, para diferentes combustíveis e diâmetros de bocais. A correlação proposta apresentou boa concordância com os resultados experimentais. A partir das análises desenvolvidas neste trabalho, verificou-se que a velocidade de blowout de chamas de difusão turbulenta é função das propriedades do combustível, das características do bocal, das condições do ambiente e do adimensional número de Damköhler. / The study of flame stability is very important to the design of burners used in industrial ovens and furnaces, combustion chambers of gas turbines and flares; and fuel substitution in burners. There is a range of conditions (for example gas velocity at the nozzle exit and jet fuel concentration in the gas mixture) at which stable combustion can be maintained, being limited by two phenomena called liftoff and blowout. Lift-off is the detachment of the flame from the fuel nozzle, and blowout its detachment and extinction. Operating conditions close to stability limits should be avoided for security reasons. Many theories have been published to describe the blowout and lifted characteristics of turbulent jet diffusion flames. This document presents some theories, as well as the assumptions and physical processes considered responsible for these phenomena (liftoff and blowout). Correlations for predicting the blowout velocity and experimental results available in the literature are also shown. A new correlation is proposed, which is based on large-scale motions observed in turbulent jets and the dimensionless Damköhler number (ratio of the characteristic chemical reaction time and the time associated with the mixing of reentrained hot products into fresh reactants). Comparisons between the predictions of the proposed correlation with experimental results and predictions of other correlations available in the literature were performed for different fuels and nozzle diameters. The proposed correlation showed good agreement with the experimental results. The analyses developed in this work allow us to conclude that the blowout velocity of the turbulent diffusion flame depends on the fuel properties, characteristics of the nozzle, the environmental conditions and the Damköhler number.

This thesis explores the effects of operating parameters on the location and shape of lifted flames in a Low Swirl Burner (LSB). In addition, it details the development and analysis of a CH PLIF imaging system for visualizing flames in lean combustion systems. The LSB is studied at atmospheric pressure using LDV and CH PLIF. CH* chemiluminescence is used for high pressure flame imaging. A four-level model of the fluorescing CH system is developed to predict the signal intensity in hydrocarbon flames. Results from imaging an atmospheric pressure laminar flame are used to validate the behavior of the signal intensity as predicted by the model. The results show that the fluorescence signal is greatly reduced at high pressure due to the decreased number of CH molecules and the increased collisional quenching rate. This restricts the use of this technique to increasingly narrow equivalence ratio ranges at high pressures. The limitation is somewhat alleviated by increasing the preheat temperature of the reactant mixture. The signal levels from high hydrogen-content syngas mixtures doped with methane are found to be high enough to make CH PLIF a feasible diagnostic to study such flames. Finally, the model predicts that signal levels are unlikely to be significantly affected by the presence of strain in the flow field, as long as the flames are not close to extinction. The results from the LSB flame investigation reveal that combustor provides reasonably robust flame stabilization at low and moderate values of combustor pressure and reference velocities. However, at very high velocities and pressures, the balance between the reactant velocity and the turbulent flame speed shifts in favor of the former resulting in the flame moving downstream. The extent of this movement is small, but indicates a tendency towards blow off at higher pressures and velocities that may be encountered in real world gas turbine applications. There is an increased tendency of relatively fuel-rich flames to behave like attached flames at high pressure. These results raise interesting questions about turbulent combustion at high pressure as well as provide usable data to gas turbine combustor designers by highlighting potential problems.

Air pollution regulations have driven modern power generation systems to move from diffusion to premixed combustion. However, these premixed combustion systems are prone to combustion instability, causing high fluctuations in pressure and temperature. This results in shortening of component life, system failure, or even catastrophic disasters. A large number of studies have been performed to understand and quantify the onset of combustion instability and the limit cycle amplitude. However, much work remains due to the complexity of the process associated with flow dynamics and chemistry. This thesis focuses on identifying, quantifying and predicting mechanisms of flame response subject to disturbances. A promising tool for predicting combustion instability is a flame transfer function. The flame transfer function is obtained by integrating unsteady heat release over the combustor domain. Thus, the better understanding of spatio-temporal characteristics of flame is required to better predict the flame transfer function. The spatio-temporal flame response is analyzed by the flame kinematic equation, so called G-equation. The flame is assumed to be a thin interface separating products and reactant, and the interface is governed by the local flow and the flame propagation. Much of the efforts were done to the flame response subject to the harmonic velocity disturbance. A key assumption allowing for analytic solutions is that the velocity is prescribed. For the mathematical tools, small perturbation theory, Hopf-Lax formula and numerical simulation were used. Solutions indicated that the flame response can be divided into three regions, referred to here as the near-field, mid-field, and farfield. In each regime, analytical expressions were derived, and those results were compared with numerical and experimental data. In the near field, it was shown that the flame response grows linearly with the normal component of the velocity disturbance. In the mid field, the flame response shows peaks in gain, and the axial location of these peaks can be predicted by the interference pattern by two characteristic waves. Lastly, in the far field where the flame response decreases, three mechanisms are studied; they are kinematic restoration, flame stretch, and turbulent flow effects. For each mechanism, key parameters are identified and their relative significances are compared.