In recent years, the development and use of biofuels have received considerable attention due to the high demand for environmentally acceptable (green) fuels. Most of the recent studies have looked at the processes of converting vegetable oils into biodiesel. It is well known vegetable oil to biodiesel conversion involves many processes including transesterification, which makes biodiesel costly and time-consuming to produce. In this study, the effects of blending high-viscosity fresh and used corn oils with low-viscosity diesel and jet fuel mixed with butanol and ethanol were studied. Several corn oil-based blends were formulated and characterized to understand the effect of composition on viscosity, fuel stability and energy content. The formulated corn oil blends were combusted in a 30 kW modified combustion chamber to determine the corresponding NOx and CO emission levels, along with CO₂ levels. Used corn oil was made by simply heating fresh corn oil for a fixed period of time (about 44 hours), and was characterized by quantifying its total polar material (TPM), iodine value, free fatty acid content, and peroxide value. The combustion experiments were conducted at a constant heat output of 68,620 kJ/hr (19 kW), to observe and study the effects of equivalence ratio, swirl number, and fuel composition on emissions. Used corn oil blends exhibited better combustion performance than fresh corn oil blends, due in part to the higher unsaturation levels in fresh corn oil. NOx emissions for used corn oil increased with swirl number. Among all the blends, the one with the higher amount of diesel (lower amount of corn oil) showed higher NOx emissions. The blend with fresh corn oil showed decreasing NOx with increasing equivalence ratio at swirl number 1.4. All blends showed generally decreasing CO trends at both swirl numbers at very lean conditions. The diesel fuel component as well as the alcohols in the blends were also important in the production of pollutants. Compared to the diesel-based blends mixed with used corn oil, butanol, and ethanol, the jet fuel-based blends showed higher NOx levels and lower CO levels at both swirl numbers.

Systematic parametric studies were performed to better understand seal-inlet rotordynamics. A CFD-perturbation model was employed to compute the seal-inlet flow disturbance quantities. Seal inlet disturbance boundary condition correlations were proposed from the computed seal-inlet quantities using the important parameters. It was found that the cosine component of the seal-inlet swirl velocity disturbance W1C has a substantial impact on the cross-coupled stiffness, and that the correlations for W1C and W1S should be used to replace the historical guess that seal inlet W1C = 0 and W1S = 0. Also, an extremely precise relationship was found between the swirl disturbance W1C and the seal-inlet swirl velocity (ωRsh − ¯W0). Thus, the number of experiments or computer runs needed to determine the effect of spin speed, shaft radius and/or inlet swirl velocity on the cross-coupled stiffness is greatly reduced by plotting the simplified relationship of the cross-coupled stiffness against the swirl slip velocity. The benefits of using the new seal-inlet boundary condition correlations were assessed by implementing them into a CFD-perturbation model. Consistently improved agreement with measurements was obtained for both liquid annular seals and gas labyrinth seals. Further, the well-established CFD-perturbation model with new boundary condition correlations was employed to investigate the rotordynamics of two off-design situations. The first case considered the influence of labyrinth seal teeth damage on the performance and the rotordynamic characteristics of impeller eye seals in centrifugal compressors. The second case considered the influence of rotor-axial-shifting on rotordynamic forces for high-low labyrinth seals in steam turbines during the start-up and shut-down process. The results should provide useful information for labyrinth seal design and fault diagnosis of stability problems in turbines and compressors.

O desenvolvimento de queimadores de baixo NOx é baseado na compreensão da interação entre a cinética química da combustão e o campo do escoamento. Escoamentos rotacionais (swirling flows) são caracterizados pela presença de gradientes de pressão radiais e axiais, e tem sido aplicados como técnica de combustão para a minimização desses poluentes. Neste trabalho é apresentada a modelagem numérica de uma câmara de combustão cilíndrica com queimador dotado com swirler de blocos móveis. O modelo, composto pela equação de continuidade, balanços da quantidade de movimento em três dimensões, o transporte da energia cinética turbulenta e da vorticidade, transporte de espécies químicas e energia, foi implementado numericamente sob a plataforma computacional Fluent. A câmara foi simulada considerando propano combustível e os resultados comparados a dados experimentais de uma câmara cilíndrica operada com GLP. Como principal resultado foi possível identificar a ocorrência da ZCR no escoamento e a influência do número de swirl sobre as características da combustão. / The development of low NOx burners is based on the comprehension of the interaction between combustion kinetics and flow field. Swirling flows are characterized by radial and axial pressure gradients, which improve the recirculation of the hot products into the flame region, and then enhance the combustion efficiency have being proposed as a mean to reduce NOx emissions from these equipment’s. This work presents the numerical modeling of cylindrical combustion chamber equipped with movable blocks burner. The model includes the continuity equation along with the 3D momentum balance equations, the k-ω shear stress transport turbulence model equations, the energy balance and the equations for transport chemical species. Results of the simulation of the swirling reactive flow in the combustion chamber, performed using Fluent CFD package, are validated by comparison with experimental data obtained elsewhere. As a main result, it was possible to identify the occurrence of a CRZ in the flow and to discuss the influence of the swirl number on the combustion characteristics.

O desenvolvimento de queimadores de baixo NOx é baseado na compreensão da interação entre a cinética química da combustão e o campo do escoamento. Escoamentos rotacionais (swirling flows) são caracterizados pela presença de gradientes de pressão radiais e axiais, e tem sido aplicados como técnica de combustão para a minimização desses poluentes. Neste trabalho é apresentada a modelagem numérica de uma câmara de combustão cilíndrica com queimador dotado com swirler de blocos móveis. O modelo, composto pela equação de continuidade, balanços da quantidade de movimento em três dimensões, o transporte da energia cinética turbulenta e da vorticidade, transporte de espécies químicas e energia, foi implementado numericamente sob a plataforma computacional Fluent. A câmara foi simulada considerando propano combustível e os resultados comparados a dados experimentais de uma câmara cilíndrica operada com GLP. Como principal resultado foi possível identificar a ocorrência da ZCR no escoamento e a influência do número de swirl sobre as características da combustão. / The development of low NOx burners is based on the comprehension of the interaction between combustion kinetics and flow field. Swirling flows are characterized by radial and axial pressure gradients, which improve the recirculation of the hot products into the flame region, and then enhance the combustion efficiency have being proposed as a mean to reduce NOx emissions from these equipment’s. This work presents the numerical modeling of cylindrical combustion chamber equipped with movable blocks burner. The model includes the continuity equation along with the 3D momentum balance equations, the k-ω shear stress transport turbulence model equations, the energy balance and the equations for transport chemical species. Results of the simulation of the swirling reactive flow in the combustion chamber, performed using Fluent CFD package, are validated by comparison with experimental data obtained elsewhere. As a main result, it was possible to identify the occurrence of a CRZ in the flow and to discuss the influence of the swirl number on the combustion characteristics.

abstract: A new theoretical model was developed utilizing energy conservation methods in order to determine the fully-atomized cross-sectional Sauter mean diameters of pressure-swirl atomizers. A detailed boundary-layer assessment led to the development of a new viscous dissipation model for droplets in the spray. Integral momentum methods were also used to determine the complete velocity history of the droplets and entrained gas in the spray. The model was extensively validated through comparison with experiment and it was found that the model could predict the correct droplet size with high accuracy for a wide range of operating conditions. Based on detailed analysis, it was found that the energy model has a tendency to overestimate the droplet diameters for very low injection velocities, Weber numbers, and cone angles. A full parametric study was also performed in order to unveil some underlying behavior of pressure-swirl atomizers. It was found that at high injection velocities, the kinetic energy in the spray is significantly larger than the surface tension energy, therefore, efforts into improving atomization quality by changing the liquid's surface tension may not be the most productive. From the parametric studies it was also shown how the Sauter mean diameter and entrained velocities vary with increasing ambient gas density. Overall, the present energy model has the potential to provide quick and reasonably accurate solutions for a wide range of operating conditions enabling the user to determine how different injection parameters affect the spray quality. / Dissertation/Thesis / M.S. Aerospace Engineering 2013

No description available.

Neste trabalho pretende-se desenvolver o dispositivo para a fixação de cabeçotes e acionamento de válvulas em um equipamento para medição de swirl, que é um dos movimentos do ar dentro da câmara de combustão nos motores de ignição por compressão. Este desenvolvimento tem como objetivos facilitar a montagem do cabeçote no equipamento e desenvolver o avanço automático das válvulas, visando a redução do tempo total do ensaio. No desenvolvimento, foi feito um comparativo das características e componentes montados nos cabeçotes e nos diferentes modelos que serão testados no equipamento, para que não fossem necessários retrabalhos no cabeçote ou desmontagens de componentes para a realização dos ensaios, abrangendo a maior gama possível de produtos. Foram definidos os métodos de posicionamento do cabeçote no dispositivo e o sistema de fixação. Para garantir a precisão no acionamento das válvulas, foi definido um fuso de esferas recirculantes, acionadas por um motor de passo. O projeto foi concluído e o dispositivo foi fabricado e instalado no equipamento de medição. Testes realizados mostraram resultados de medição de swirl conforme esperado, além da diminuição no tempo total do teste. A partir de observações feitas após a fabricação e os testes no dispositivo, algumas melhorias estão sendo propostas, como, por exemplo, acionamentos por balancins independentes para cada válvula. / In this work, the aim is to develop the device for the fixture of the cylinder head and the valve actuation in a swirl meter test bench. Swirl is a movement inside the combustion chamber in a compression ignition engine. The development aims to facilitate the assembling of the cylinder head in the equipment and develop the valve lift device, focusing in decreasing the total time for the test. Also, the valve actuator shall be able to perform the continuous valve lift in the swirl measurement. During the development of this work, a comparative of the main features and the components assembled in the different cylinder head types to be tested in the equipment was done, to avoid rework or disassembling of components for the test, including the most variety of types. It was defined the positioning method for cylinder head in the device and the fixation system. To ensure the precision in the valve actuation, it was defined a ball screw, driven by a step motor. The project was finalized, manufactured and installed in the measurement equipment. Performed tests have showed results of swirl measurement according to expected, and the total time of test was decreased. After this first project, some improvements are proposed in the device, for example, individual actuation per valve.

Characterization of distortion transfer and generation through fans with distorted inlet conditions enables progress towards designs with improved distortion tolerance. The abruptness of transition from undistorted to distorted total pressure regions at the inlet impacts the induced swirl profile and therefore the distortion transfer and generation. These impacts are characterized using URANS simulations of PBS Rotor 4 geometry under a variety of inlet distortion profiles. A 90° and a 135° sector, both of 15% total pressure distortion, are considered. Variants of each sector size, with decreasing levels of distortion transition abruptness, are each applied to the fan. Fourier-based distortion descriptors are used to quantify levels of distortion transfer and generation at axial locations through the fan, principally at the stator inlet. It is shown that a gradual transition in distortion at the inlet results in decreased levels of distortion transfer and generation. The flow physics resulting in this reduction are explored. URANS simulations involving turbomachinery are complex and often require simplifying assumptions to balance computational costs with accuracy. One assumption removes the need for a nozzle to control nozzle operation condition and replaces it with a static pressure boundary condition located at the stator exit. This assumption is challenged by conducting a series of distorted inlet simulations with a nozzle, which are then compared to a corresponding set of simulations conducted using the exit boundary assumption. Performance parameters for each set of simulations are compared. Performance was observed to be within 1% difference between the two methods, supporting the assumption that a static pressure boundary is adequate for controlling inlet distortion simulations. Finally, full annulus URANS simulations are presented to investigate distortion phase shift in a single stage transonic fan. The fan is subject to a 90° sector inlet total pressure distortion. Simulation results are presented for choke, design, and near-stall operating conditions. Circumferential profiles of swirl, total pressure, total temperature, power, and phase shift are analyzed at 10%, 30%, 50%, 70%, and 90% span. Several metrics for phase shift, which is a measure of the rotational translation of a distortion profile, are presented and compared. Each aims to assist understanding the translational motion of distortion as it passes through the fan. The different metrics used for phase shift are used to analyze distortion phase. Insights from each are presented alongside limitations for each method. A combination of methods is proposed to address their respective limitations.

Air velocity and fuel concentration data have been collected throughout the flow fields of two gas turbine mixers in an effort to better understand the mixing of fuel and air in gas turbine mixers. The two gas turbine mixers consisted of an annular flow profile and incorporated swirl vanes to produce a swirling flow to promote fuel/air mixing. The fuel was injected into the bulk flow from the pressure side of the swirl vanes. The first mixer had a swirl angle of 45°, while the second had a swirl angle of 55°. In order to examine the effect of the swirl angle on the mixing of fuel and air as the flow progressed through gas turbine mixers, axial and tangential air velocity data was taken using a laser Doppler velocimeter (LDV). Also, fuel concentration data was taken separately using a hydrocarbon concentration probe with methane diluted with air as the fuel. The data were taken at varying axial and varying angular locations in an effort to capture the spatial development of the fuel and velocity profiles. The spectra of the data were analyzed as well in an effort to understand the turbulence of the flow. It was found that the 55° swirler exhibited smaller variations in both velocity and fuel concentration values and that the fuel reached a uniform concentration at axial locations further upstream in the 55° degree mixer than in the 45° mixer. The RMS values of the velocity, which were influenced by the swirl vanes, were higher in the 55° mixer and likely contributed to the better mixing performance of the 55° mixer. The fuel concentration spectrum data showed that the spectra of the two mixers were similar, and that the fluctuations in fuel concentration due to flow emanating from the swirl vanes were seen throughout the length of the two mixers.

Next generation aircraft design focuses on highly integrated airframe/engine architectures that exploit advantages in system level efficiency and performance. One such design concept incorporates boundary layer ingestion which locates the turbofan engine inlet near enough to the lifting surface of the aircraft skin that the boundary layer is ingested and reenergized. This process reduces overall aircraft drag and associated required thrust, resulting in fuel savings and decreased emissions; however, boundary layer ingestion also creates unique challenges for the turbofan engines operating in less than optimal inlet flow conditions. The engine inlet flow profiles predicted from boundary layer ingesting aircraft architectures contain complex distortions that affect the engine operability, durability, efficiency, and performance. One component of these complex distortion profiles is off-axial secondary flow, commonly referred to as swirl. As a means to investigate the interactions of swirl distortion with turbofan engines, an experiment was designed to measure distorted flow profiles in an operating turbofan research engine. Three-dimensional flow properties were measured at discrete planes immediately upstream and immediately downstream of the fan rotor, isolating the component for analysis. Constant speed tests were conducted under clean and distorted test conditions. For clean tests, a straight cylindrical inlet duct was attached to the fan case; for distorted tests, a StreamVane swirl distortion generator was inserted into the inlet duct. The StreamVane was designed to induce a swirl distortion matching results of computation fluid dynamics models of a conceptual blended wing body aircraft at a plane upstream of the fan. The swirl distortion was then free to develop naturally within the inlet duct before being ingested by the engine. Results from the investigation revealed that the generated swirl profile developed, mixed, and dissipated in the inlet duct upstream of the fan. Measurements immediately upstream of the fan rotor leading edge revealed 50% reduction in measured flow angle magnitudes along with evidence of fanwise vortex convection when compared to the StreamVane design profile. The upstream measurements also indicated large amounts of secondary flow entered the fan rotor. Measurements immediately downstream of the fan rotor trailing edge demonstrated that the fan processed the distortion and further reduced the intensity of the swirl; however, non-uniform secondary flow persisted at this plane. The downstream measurements confirmed that off-design conditions entered the fan exit guide vanes, likely contributing to cascading performance deficiencies in downstream components and reducing the performance of the propulsor system. / Master of Science