This thesis describes an experimental investigation of high frequency acoustic wave scattering from turbulent premixed flames. The objective of this work was to characterize the scattered incoherent acoustic field and determine its parametric dependence on frequency, flame brush thickness, incident and measurement angles, mean velocity and flame speed. The experimental facility consists of a slot burner with a flat flame sheet that is approximately 15 cm wide and 12 cm tall. The baseline cold flow characteristics and flame sheet statistics were extensively characterized. Studies were performed over a wide range of frequencies (1-24 kHz) in order to characterize the role of the incident acoustic wave length. The spectrum of the scattered acoustic field showed distinct incoherent spectral sidebands on either side of the driving frequency. The scattered incoherent field was characterized in terms of the incoherent field strength and spectral bandwidth and related to the theoretical predictions. The role of the flame front wrinkling scale, i.e., flame brush thickness, was also studied. Flame brush thickness was varied independent of the mean velocity and flame speed by using a variable turbulence generator. Results are reported for five flame brush thickness cases, ranging from 1.2 mm to 5.2 mm. Some dependence of scattered field characteristics on flame brush thickness was observed, but the magnitude of the effect was much smaller than expected from theoretical considerations. The spatial dependence of the scattered field was investigated by measuring the scattered field at four measurement angles and exciting the flame at four incident angles. Theory predicts that these variations influence the spatial scale of the acoustic wave normal to the flame, a result confirmed by the measurements. Measurements were performed for multiple combinations of mean velocities and flame speeds. The scattered field was observed to depend strongly on the flame speed. Further analysis suggested that the change in orientation angle distribution with flame speed had a large influence on the scattered field. The scattered field characteristics did not show any appreciable change with mean velocity. This result was expected since flame brush thickness characteristics themselves exhibit a weak velocity dependence.

Gas turbine engines for aircraft applications are required to meet multiple performance and sizing requirements, subject to constraints established by the best available technology level. The performance requirements and limiting values of constraints that are considered by the cycle analyst conducting an engine cycle design occur at multiple operating conditions. The traditional approach to cycle analysis chooses a single design point with which to perform the on-design analysis. Additional requirements and constraints not transpiring at the design point must be evaluated in off-design analysis and therefore do not influence the cycle design. Such an approach makes it difficult to design the cycle to meet more than a few requirements and limits the number of different aerothermodynamic cycle designs that can reasonably be evaluated. Engine manufacturers have developed computational methods to create aerothermodynamic cycles that meet multiple requirements, but such methods are closely held secrets of their design process. This thesis presents a transparent and publicly available on-design cycle analysis method for gas turbine engines which generates aerothermodynamic cycles that simultaneously meet performance requirements and constraints at numerous design points. Such a method provides the cycle analyst the means to control all aspects of the aerothermodynamic cycle and provides the ability to parametrically create candidate engine cycles in greater numbers to comprehensively populate the cycle design space from which a "best" engine can be selected. This thesis develops the multi-design point on-design cycle analysis method labeled simultaneous MDP. The method is divided into three different phases resulting in an 11 step process to generate a cycle design space for a particular application. Through implementation of simultaneous MDP, a comprehensive cycle design space can be created quickly for the most complex of cycle design problems. Furthermore, the process documents the creation of each candidate engine providing transparency as to how each engine cycle was designed to meet all of the requirements. The simultaneous MDP method is demonstrated in this thesis on a high bypass ratio, separate flow turbofan with up to 25 requirements and constraints and 9 design points derived from a notional 300 passenger aircraft.

Thesis (M.App.Sc.) - Carleton University, 2005. / Includes bibliographical references (p. 174-179). Also available in electronic format on the Internet.

Thesis (M.App.Sc.) - Carleton University, 2006. / Includes bibliographical references (p. 110-113). Also available in electronic format on the Internet.

Thesis (Ph.D.) - Carleton University, 2007. / Includes bibliographical references (p. 249-266). Also available in electronic format on the Internet.

Thesis (M.S.)--Florida State University, 2006. / Advisor: Juan C. Ordonez, Florida State University, College of Engineering, Dept. of Mechanical Engineering. Title and description from dissertation home page (viewed Sept. 15, 2006). Document formatted into pages; contains viii, 78 pages. Includes bibliographical references.

abstract: Gas turbine efficiency has improved over the years due to increases in compressor pressure ratio and turbine entry temperature (TET) of main combustion gas, made viable through advancements in material science and cooling techniques. Ingestion of main combustion gas into the turbine rotor-stator disk cavities can cause major damage to the gas turbine. To counter this ingestion, rim seals are installed at the periphery of turbine disks, and purge air extracted from the compressor discharge is supplied to the disk cavities. Optimum usage of purge air is essential as purge air extraction imparts a penalty on turbine efficiency and specific fuel consumption. In the present work, experiments were conducted in a newly constructed 1.5-stage axial flow air turbine featuring vanes and blades to study main gas ingestion. The disk cavity upstream of the rotor, the 'front cavity', features a double seal with radial clearance and axial overlap at its rim. The disk cavity downstream of the rotor, the 'aft cavity', features a double seal at its rim but with axial gap. Both cavities contain a labyrinth seal radially inboard; this divides each disk cavity into an 'inner cavity' and a 'rim cavity'. Time-averaged static pressure at various locations in the main gas path and disk cavities, and tracer gas (CO2) concentration at different locations in the cavities were measured. Three sets of experiments were carried out; each set is defined by the main air flow rate and rotor speed. Each of the three sets comprises of four different purge air flow rates, low to high. The mass flow rate of ingested main gas into the front and aft rim cavities is reported at the different purge air flow rates, for the three experiment sets. For the present stage configuration, it appears that some ingestion persisted into both the front and aft rim cavities even at high purge air flow rates. On the other hand, the front and aft inner cavity were completely sealed at all purge flows. / Dissertation/Thesis / Masters Thesis Engineering 2015

Esta dissertação de mestrado apresenta o desenvolvimento de um trabalho que tem como objetivos avaliar a composição de turbocompressores veiculares para microgeração de energia e desenvolver um modelo de câmara de combustão tubular para equipar microturbinas a gás derivadas de turbocompressores. No desenvolvimento do trabalho, utilizando o software Cycle-Tempo, foi feita a avaliação de possíveis configurações de microturbinas a gás derivadas de turbocompressores, no que diz respeito ao número de eixos e dispositivos de aumento de eficiência térmica (intercooler, recuperador de calor e reaquecedor). No total foram simuladas, dez diferentes configurações, sendo que as análises foram feitas diretamente nos parâmetros de eficiência térmica dos conjuntos avaliando-se a relação entre a energia aportada pelo combustível e a energia entregue num gerador elétrico hipotético. Na sequência são definidos os turbocompressores para compor uma determinada configuração de microturbina a gás e, para tanto, utilizaram-se os mapas de desempenho dos turbocompressores de um fabricante. A partir dos parâmetros de operação dos equipamentos foi desenvolvido um modelo tridimensional de câmara de combustão em software de CAD. O modelo passou por cinco etapas de simulações em Dinâmica dos Fluidos Computacional (Computational Fluid Dynamics - CFD). As primeiras três etapas serviram para desenvolver e aprimorar o modelo tridimensional de câmara de combustão e, por limitações do software, não envolveram combustão. Utilizando condições de contorno operacionais, foram avaliados: o perfil de velocidades ao longo da câmara de combustão, a perda de pressão, a intensidade da turbulência, a homogeneização entre os reagentes ar e combustível e a divisão do fluxo mássico em cada seção da câmara de combustão. A partir do modelo tridimensional foi desenvolvido um protótipo da câmara de combustão, construído a partir de tubos comerciais de PVC. O protótipo foi avaliado experimentalmente com escoamento do ar a temperatura ambiente, utilizando o acoplamento em série entre um ventilador centrífugo e um soprador. No experimento foi avaliada a divisão de fluxo mássico de ar em cada seção da câmara de combustão e a perda de pressão. As simulações CFD foram refeitas na quarta etapa, onde as condições de contorno foram os parâmetros de fluxo mássico, pressão e temperatura, obtidos experimentalmente. Com isto, pode ser feita a comparação direta entre os resultados obtidos experimentalmente e os resultados das simulações CFD. Concluindo o trabalho foi realizada a quinta etapa, onde foi inserida uma fonte de calor simulando o aporte de energia da combustão, permitindo a avaliação da temperatura na câmara de combustão. As simulações CFD indicaram resultados semelhantes ao que é previsto em bibliografia, no que diz respeito à divisão do fluxo mássico, perda de pressão e à distribuição de velocidades. Já as avaliações experimentais apresentaram incerteza de medição elevada para a divisão de fluxo mássico. Quanto à perda de pressão o método experimental mostrou-se adequado. / Submitted by Ana Guimarães Pereira (agpereir@ucs.br) on 2017-10-25T17:02:08Z No. of bitstreams: 1 Dissertacao Daniel Vieira Pinto.pdf: 7889874 bytes, checksum: a3dd417da94a3175c511cb73b3577fd2 (MD5) / Made available in DSpace on 2017-10-25T17:02:08Z (GMT). No. of bitstreams: 1 Dissertacao Daniel Vieira Pinto.pdf: 7889874 bytes, checksum: a3dd417da94a3175c511cb73b3577fd2 (MD5) Previous issue date: 2017-10-25 / This master's work presents the development of a work that has the objective of evaluating the composition of vehicular turbochargers for microgeneration of energy and to develop a tubular combustion chamber model to equip gas microturbines derived from turbochargers. In the development of the work, using the software Cycle-Tempo, it is made the evaluation of possible configurations of gas micro turbines derived from turbochargers, with respect to the number of axes and devices of increasing thermal efficiency (intercoolers, heat recover e reheater). In total, ten different configurations were simulated, and the analyzes were done directly in the thermal efficiency parameters of the sets, evaluating the relation between the energy contributed by the fuel and the energy delivered in a hypothetical electric generator. Turbochargers are then defined to form a particular gas micro turbine configuration and, being used the turbocharger performance maps from a manufacturer. From the operating parameters of the equipment, a three-dimensional combustion chamber model was developed in CAD software. The model went through five stages of simulations in Computational Fluid Dynamics (CFD). The first three steps served to develop and improve the three-dimensional model of combustion chamber and, due to software limitations, did not involve combustion. Using operational contour conditions, the velocity profile along the combustion chamber, the pressure loss, the turbulence intensity, the homogenization between the air and fuel reactants and the division of the mass flow in each section of the combustion chamber were evaluated. From the three-dimensional model was developed a prototype of the combustion chamber, built from commercial PVC pipes. The prototype was evaluated experimentally with air flow at room temperature using the coupling in series between a centrifugal fan and a blower. In the experiment the air mass flow division in each section of the combustion chamber and the loss of pressure were evaluated. The CFD simulations were redone in the fourth stage, where the boundary conditions were the parameters of mass flow, pressure and temperature, obtained experimentally. Thus, a direct comparison between the results obtained experimentally and the results of CFD simulations can be made. At the end of the work the fifth step was performed, where a heat source was inserted simulating the energy input of the combustion, allowing the temperature evaluation in the combustion chamber. The CFD simulations indicated results similar to those predicted in the literature, regarding the division of mass flow, pressure loss and velocity distribution. However, the experimental evaluations presented high measurement uncertainty for the mass flow division. Regarding pressure loss, the experimental method proved to be adequate.

Esta dissertação de mestrado apresenta o desenvolvimento de um trabalho que tem como objetivos avaliar a composição de turbocompressores veiculares para microgeração de energia e desenvolver um modelo de câmara de combustão tubular para equipar microturbinas a gás derivadas de turbocompressores. No desenvolvimento do trabalho, utilizando o software Cycle-Tempo, foi feita a avaliação de possíveis configurações de microturbinas a gás derivadas de turbocompressores, no que diz respeito ao número de eixos e dispositivos de aumento de eficiência térmica (intercooler, recuperador de calor e reaquecedor). No total foram simuladas, dez diferentes configurações, sendo que as análises foram feitas diretamente nos parâmetros de eficiência térmica dos conjuntos avaliando-se a relação entre a energia aportada pelo combustível e a energia entregue num gerador elétrico hipotético. Na sequência são definidos os turbocompressores para compor uma determinada configuração de microturbina a gás e, para tanto, utilizaram-se os mapas de desempenho dos turbocompressores de um fabricante. A partir dos parâmetros de operação dos equipamentos foi desenvolvido um modelo tridimensional de câmara de combustão em software de CAD. O modelo passou por cinco etapas de simulações em Dinâmica dos Fluidos Computacional (Computational Fluid Dynamics - CFD). As primeiras três etapas serviram para desenvolver e aprimorar o modelo tridimensional de câmara de combustão e, por limitações do software, não envolveram combustão. Utilizando condições de contorno operacionais, foram avaliados: o perfil de velocidades ao longo da câmara de combustão, a perda de pressão, a intensidade da turbulência, a homogeneização entre os reagentes ar e combustível e a divisão do fluxo mássico em cada seção da câmara de combustão. A partir do modelo tridimensional foi desenvolvido um protótipo da câmara de combustão, construído a partir de tubos comerciais de PVC. O protótipo foi avaliado experimentalmente com escoamento do ar a temperatura ambiente, utilizando o acoplamento em série entre um ventilador centrífugo e um soprador. No experimento foi avaliada a divisão de fluxo mássico de ar em cada seção da câmara de combustão e a perda de pressão. As simulações CFD foram refeitas na quarta etapa, onde as condições de contorno foram os parâmetros de fluxo mássico, pressão e temperatura, obtidos experimentalmente. Com isto, pode ser feita a comparação direta entre os resultados obtidos experimentalmente e os resultados das simulações CFD. Concluindo o trabalho foi realizada a quinta etapa, onde foi inserida uma fonte de calor simulando o aporte de energia da combustão, permitindo a avaliação da temperatura na câmara de combustão. As simulações CFD indicaram resultados semelhantes ao que é previsto em bibliografia, no que diz respeito à divisão do fluxo mássico, perda de pressão e à distribuição de velocidades. Já as avaliações experimentais apresentaram incerteza de medição elevada para a divisão de fluxo mássico. Quanto à perda de pressão o método experimental mostrou-se adequado. / This master's work presents the development of a work that has the objective of evaluating the composition of vehicular turbochargers for microgeneration of energy and to develop a tubular combustion chamber model to equip gas microturbines derived from turbochargers. In the development of the work, using the software Cycle-Tempo, it is made the evaluation of possible configurations of gas micro turbines derived from turbochargers, with respect to the number of axes and devices of increasing thermal efficiency (intercoolers, heat recover e reheater). In total, ten different configurations were simulated, and the analyzes were done directly in the thermal efficiency parameters of the sets, evaluating the relation between the energy contributed by the fuel and the energy delivered in a hypothetical electric generator. Turbochargers are then defined to form a particular gas micro turbine configuration and, being used the turbocharger performance maps from a manufacturer. From the operating parameters of the equipment, a three-dimensional combustion chamber model was developed in CAD software. The model went through five stages of simulations in Computational Fluid Dynamics (CFD). The first three steps served to develop and improve the three-dimensional model of combustion chamber and, due to software limitations, did not involve combustion. Using operational contour conditions, the velocity profile along the combustion chamber, the pressure loss, the turbulence intensity, the homogenization between the air and fuel reactants and the division of the mass flow in each section of the combustion chamber were evaluated. From the three-dimensional model was developed a prototype of the combustion chamber, built from commercial PVC pipes. The prototype was evaluated experimentally with air flow at room temperature using the coupling in series between a centrifugal fan and a blower. In the experiment the air mass flow division in each section of the combustion chamber and the loss of pressure were evaluated. The CFD simulations were redone in the fourth stage, where the boundary conditions were the parameters of mass flow, pressure and temperature, obtained experimentally. Thus, a direct comparison between the results obtained experimentally and the results of CFD simulations can be made. At the end of the work the fifth step was performed, where a heat source was inserted simulating the energy input of the combustion, allowing the temperature evaluation in the combustion chamber. The CFD simulations indicated results similar to those predicted in the literature, regarding the division of mass flow, pressure loss and velocity distribution. However, the experimental evaluations presented high measurement uncertainty for the mass flow division. Regarding pressure loss, the experimental method proved to be adequate.

Due to a relative high thermal efficiency, the gas turbine engine has wide ranging applications in various industries today. The aerospace and power generation sectors are probably the best known. One method of increasing the thermal efficiency of a gas turbine engine is to increase the turbine inlet temperature. This increase in temperature will result in an additional thermal load being placed on the turbine blades and in particular the nozzle guide vanes. The higher temperature gradients will increase the thermal stresses. In order to prevent failure of blades due to thermal stresses, it is important to accurately determine the magnitude of the stresses during the design phase of an engine. The accuracy of the thermal stresses mainly depends on two issues. The first is the determination of the heat transfer from the fluid to the blade and then secondly the prediction of the thermal stresses in the blade as a result of the thermal loading. In this study the flow and heat transfer problem is approached through the use of computational fluid dynamics (CFD). The principal focus is to predict the heat transfer and thermal stresses for steady state cases for both cooled and uncooled nozzle guide vanes through numerical modelling techniques. From the literature, two studies have been identified for which experimental data was available. These case studies can therefore be used to evaluate the accuracy of using CFD to simulate the thermal loading on the blades. One study focused only on solving heat transfer whilst the other included thermal stress modelling. The same methodology is then applied to a three-dimensional application in which flow and heat transfer was solved for a nozzle guide vane of a commercial gas turbine engine. The accuracy of results varied with the choice of turbulence model but was, generally within ten percent of experimental data. It was shown that the accurate determination of the heat transfer to the blade is the key element to accurately determine the thermal stresses. / Dissertation (M Eng (Mechanical Engineering))--University of Pretoria, 2006. / Mechanical and Aeronautical Engineering / unrestricted