The aim of this work is to study the in-vitro aerodynamic performance of a new inhaled theophylline formulation prepared by supercritical fluids technique. For the analysis of the output from the in-vitro tests (and further in-vivo tests) a new, fast, sensitive high performance liquid chromatographic (HPLC) method was developed and validated for the determination of theophylline and other related derivatives in aqueous and urine samples using new packing materials (monolithic columns). These columns achieve efficient separation under lower backpressure and shorter time comparing to other traditionally or newly introduced C18 columns. Solution enhanced dispersion by supercritical fluid (SEDS) process has been applied for the production of anhydrous theophylline as pure crystals in the range 2-5 μm to be used as new inhaled dry powder formulation for asthma. Fifteen theophylline samples have been prepared under different experimental conditions. The drug produced by this method has been subject to a number of solid-phase analytical procedures designed to establish the crystal structure [X-ray powder diffraction (XRPD)], the structure and conformation [(FTIR), Fourier-transform Raman spectroscopy (FT-Raman)], and the morphology and particle size [scanning electron microscope (SEM)]. While, thermal gravimetric analysis (TGA), and differential scanning calorimetry (DSC) have been used to monitor any phase transition or polymorphic changes after processing. All these analytical techniques gave a satisfactory indication of the solid-state chemistry of the processed particles and assess the development of new inhalation product. The performance of inhaled SEDS theophylline with or without a carrier was evaluated using the developed HPLC method. Three samples having different particle sizes were selected out of the prepared powders by SEDS technique to be tested. The dose sampling unit and the Anderson Cascade Impactor were used to determine the in-vitro emitted dose and the deposition profiles of SEDS samples, respectively. The effect of different inhalation flows was studied using two different flows 28.3, and 60 L min-1 with 4 L inhalation volume. Different DPI devices were investigated in this study; Easyhaler® and Spinhaler®. The particle size has an important effect on the aerodynamic behaviour and deposition profile of inhaled drug, the smaller the particles the greater the total lung deposition. The presence of a carrier improves the respirable fraction for all the tested formulations.

O presente trabalho apresenta um estudo numérico e experimental sobre o desempenho aerodinâmico de turbinas eólicas de eixo vertical envolvendo rotores Savonius convencional de duplo-estágio e helicoidal. O estudo experimental é realizado no Túnel Aerodinâmico Professor Debi Pada Sadhu, do Laboratório de Mecânica dos Fluidos da UFRGS. As simulações numéricas são realizadas com o software Fluent/ANSYS utilizando o Método dos Volumes Finitos. São comparados os coeficientes de torque estático e dinâmico, o coeficiente de potência, além de uma análise aerodinâmica das duas turbinas. As medições são realizadas empregando Tubos de Pitot, um torquímetro estático digital e um torquímetro simples construído para a medição do torque dinâmico. As turbinas são fabricadas através da técnica de prototipagem 3D, com uma semelhança de dimensões e parâmetros. As soluções numéricas são resolvidas através da equação da continuidade, das equações de Navier-Stokes com médias de Reynolds (RANS) e pelo modelo de turbulência k-ω SST. A qualidade da malha utilizada é avaliada através do método de Índice de Convergência de Malha (GCI), para três diferentes tamanhos de malha. São feitas análises dos rotores na forma estática para diferentes ângulos de incidência e com a turbina em rotação são feitas análises para diferentes razões de velocidades de ponta de pá (λ). Resultados demonstram que a turbina helicoidal apresenta um coeficiente de torque positivo para todos os ângulos do rotor, assim como a turbina convencional de dois estágios. O coeficiente de torque dinâmico da turbina helicoidal é superior ao da turbina de duplo-estágio para a maioria dos casos, e também apresenta menor oscilação de torque ao longo de cada rotação. Por consequência, o coeficiente de potência do rotor helicoidal também se tornou superior, com um valor máximo encontrado na ordem de 11,8% para um λ de 0,65 no caso experimental, e de 8,4% para o mesmo λ no caso numérico, quando comparado com o rotor de duplo-estágio. Os erros relativos entre as simulações numéricas e os resultados experimentais estão entre 2,16% e 13,4%. Uma estimativa de potência gerada é feita para ambos os casos, para uma razão de velocidade de ponta de 0,65, onde a turbina helicoidal apresenta melhores resultados em relação ao rotor de duplo-estágio, na ordem de 13,6% para uma velocidade de 10,4 m/s. / This paper presents a numerical and experimental study of vertical axis wind turbine performance comparison involving two-stage and helical Savonius rotors. The experimental study is conducted in the Aerodynamic Tunnel Professor Debi Pada Sadhu at the Fluid Mechanics Laboratory of the UFRGS. The numerical simulations are performed with the Fluent/ANSYS software using the Finite Volumes Method. The static and dynamic torque coefficients, the power coefficients, and an aerodynamic analysis of the two turbines are compared. Measurements are made using Pitot tubes, a digital static torque wrench and a simple wrench constructed for the dynamic torque measurement. The aerodynamics rotors are manufactured by 3D prototyping technique with similar dimensions and parameters. Numerical solutions are solved by the continuity equation, the Reynolds Averaged Navier-Stokes (RANS) equations and the turbulence model k-ω SST. The quality of the mesh used is evaluated used the Grid Convergence Index (GCI) method, for three different mesh sizes. The rotors analyzes are made in static form for different angles of incidence and for the rotating turbine analyzes are made for differents tip speed ratio (λ). Results show that the helical turbine has a positive static torque coefficient for any rotor angles, as well as conventional two-stage turbine. The dynamic torque coefficient of the helical turbine is higher than the two-stage turbine for most cases and also shows less torque variation along each rotation. Consequently, the power coefficient of the helical rotor also become higher, with a maximum value found on the order of 11.8% for a λ of 0.65 in the experimental case, and 8.4% for the same λ number when compared with the two-stage rotor. The relative errors between the numerical simulations and the experimental results are between 2.16% and 13.4%. A generated power estimate is made for both cases, for a tip speed ratio of 0.65, where the helical turbine provides better results compared to two-stage rotor in order of 13.6% for a velocity of 10.4 m/s.

O presente trabalho apresenta um estudo numérico e experimental sobre o desempenho aerodinâmico de turbinas eólicas de eixo vertical envolvendo rotores Savonius convencional de duplo-estágio e helicoidal. O estudo experimental é realizado no Túnel Aerodinâmico Professor Debi Pada Sadhu, do Laboratório de Mecânica dos Fluidos da UFRGS. As simulações numéricas são realizadas com o software Fluent/ANSYS utilizando o Método dos Volumes Finitos. São comparados os coeficientes de torque estático e dinâmico, o coeficiente de potência, além de uma análise aerodinâmica das duas turbinas. As medições são realizadas empregando Tubos de Pitot, um torquímetro estático digital e um torquímetro simples construído para a medição do torque dinâmico. As turbinas são fabricadas através da técnica de prototipagem 3D, com uma semelhança de dimensões e parâmetros. As soluções numéricas são resolvidas através da equação da continuidade, das equações de Navier-Stokes com médias de Reynolds (RANS) e pelo modelo de turbulência k-ω SST. A qualidade da malha utilizada é avaliada através do método de Índice de Convergência de Malha (GCI), para três diferentes tamanhos de malha. São feitas análises dos rotores na forma estática para diferentes ângulos de incidência e com a turbina em rotação são feitas análises para diferentes razões de velocidades de ponta de pá (λ). Resultados demonstram que a turbina helicoidal apresenta um coeficiente de torque positivo para todos os ângulos do rotor, assim como a turbina convencional de dois estágios. O coeficiente de torque dinâmico da turbina helicoidal é superior ao da turbina de duplo-estágio para a maioria dos casos, e também apresenta menor oscilação de torque ao longo de cada rotação. Por consequência, o coeficiente de potência do rotor helicoidal também se tornou superior, com um valor máximo encontrado na ordem de 11,8% para um λ de 0,65 no caso experimental, e de 8,4% para o mesmo λ no caso numérico, quando comparado com o rotor de duplo-estágio. Os erros relativos entre as simulações numéricas e os resultados experimentais estão entre 2,16% e 13,4%. Uma estimativa de potência gerada é feita para ambos os casos, para uma razão de velocidade de ponta de 0,65, onde a turbina helicoidal apresenta melhores resultados em relação ao rotor de duplo-estágio, na ordem de 13,6% para uma velocidade de 10,4 m/s. / This paper presents a numerical and experimental study of vertical axis wind turbine performance comparison involving two-stage and helical Savonius rotors. The experimental study is conducted in the Aerodynamic Tunnel Professor Debi Pada Sadhu at the Fluid Mechanics Laboratory of the UFRGS. The numerical simulations are performed with the Fluent/ANSYS software using the Finite Volumes Method. The static and dynamic torque coefficients, the power coefficients, and an aerodynamic analysis of the two turbines are compared. Measurements are made using Pitot tubes, a digital static torque wrench and a simple wrench constructed for the dynamic torque measurement. The aerodynamics rotors are manufactured by 3D prototyping technique with similar dimensions and parameters. Numerical solutions are solved by the continuity equation, the Reynolds Averaged Navier-Stokes (RANS) equations and the turbulence model k-ω SST. The quality of the mesh used is evaluated used the Grid Convergence Index (GCI) method, for three different mesh sizes. The rotors analyzes are made in static form for different angles of incidence and for the rotating turbine analyzes are made for differents tip speed ratio (λ). Results show that the helical turbine has a positive static torque coefficient for any rotor angles, as well as conventional two-stage turbine. The dynamic torque coefficient of the helical turbine is higher than the two-stage turbine for most cases and also shows less torque variation along each rotation. Consequently, the power coefficient of the helical rotor also become higher, with a maximum value found on the order of 11.8% for a λ of 0.65 in the experimental case, and 8.4% for the same λ number when compared with the two-stage rotor. The relative errors between the numerical simulations and the experimental results are between 2.16% and 13.4%. A generated power estimate is made for both cases, for a tip speed ratio of 0.65, where the helical turbine provides better results compared to two-stage rotor in order of 13.6% for a velocity of 10.4 m/s.

O presente trabalho apresenta um estudo numérico e experimental sobre o desempenho aerodinâmico de turbinas eólicas de eixo vertical envolvendo rotores Savonius convencional de duplo-estágio e helicoidal. O estudo experimental é realizado no Túnel Aerodinâmico Professor Debi Pada Sadhu, do Laboratório de Mecânica dos Fluidos da UFRGS. As simulações numéricas são realizadas com o software Fluent/ANSYS utilizando o Método dos Volumes Finitos. São comparados os coeficientes de torque estático e dinâmico, o coeficiente de potência, além de uma análise aerodinâmica das duas turbinas. As medições são realizadas empregando Tubos de Pitot, um torquímetro estático digital e um torquímetro simples construído para a medição do torque dinâmico. As turbinas são fabricadas através da técnica de prototipagem 3D, com uma semelhança de dimensões e parâmetros. As soluções numéricas são resolvidas através da equação da continuidade, das equações de Navier-Stokes com médias de Reynolds (RANS) e pelo modelo de turbulência k-ω SST. A qualidade da malha utilizada é avaliada através do método de Índice de Convergência de Malha (GCI), para três diferentes tamanhos de malha. São feitas análises dos rotores na forma estática para diferentes ângulos de incidência e com a turbina em rotação são feitas análises para diferentes razões de velocidades de ponta de pá (λ). Resultados demonstram que a turbina helicoidal apresenta um coeficiente de torque positivo para todos os ângulos do rotor, assim como a turbina convencional de dois estágios. O coeficiente de torque dinâmico da turbina helicoidal é superior ao da turbina de duplo-estágio para a maioria dos casos, e também apresenta menor oscilação de torque ao longo de cada rotação. Por consequência, o coeficiente de potência do rotor helicoidal também se tornou superior, com um valor máximo encontrado na ordem de 11,8% para um λ de 0,65 no caso experimental, e de 8,4% para o mesmo λ no caso numérico, quando comparado com o rotor de duplo-estágio. Os erros relativos entre as simulações numéricas e os resultados experimentais estão entre 2,16% e 13,4%. Uma estimativa de potência gerada é feita para ambos os casos, para uma razão de velocidade de ponta de 0,65, onde a turbina helicoidal apresenta melhores resultados em relação ao rotor de duplo-estágio, na ordem de 13,6% para uma velocidade de 10,4 m/s. / This paper presents a numerical and experimental study of vertical axis wind turbine performance comparison involving two-stage and helical Savonius rotors. The experimental study is conducted in the Aerodynamic Tunnel Professor Debi Pada Sadhu at the Fluid Mechanics Laboratory of the UFRGS. The numerical simulations are performed with the Fluent/ANSYS software using the Finite Volumes Method. The static and dynamic torque coefficients, the power coefficients, and an aerodynamic analysis of the two turbines are compared. Measurements are made using Pitot tubes, a digital static torque wrench and a simple wrench constructed for the dynamic torque measurement. The aerodynamics rotors are manufactured by 3D prototyping technique with similar dimensions and parameters. Numerical solutions are solved by the continuity equation, the Reynolds Averaged Navier-Stokes (RANS) equations and the turbulence model k-ω SST. The quality of the mesh used is evaluated used the Grid Convergence Index (GCI) method, for three different mesh sizes. The rotors analyzes are made in static form for different angles of incidence and for the rotating turbine analyzes are made for differents tip speed ratio (λ). Results show that the helical turbine has a positive static torque coefficient for any rotor angles, as well as conventional two-stage turbine. The dynamic torque coefficient of the helical turbine is higher than the two-stage turbine for most cases and also shows less torque variation along each rotation. Consequently, the power coefficient of the helical rotor also become higher, with a maximum value found on the order of 11.8% for a λ of 0.65 in the experimental case, and 8.4% for the same λ number when compared with the two-stage rotor. The relative errors between the numerical simulations and the experimental results are between 2.16% and 13.4%. A generated power estimate is made for both cases, for a tip speed ratio of 0.65, where the helical turbine provides better results compared to two-stage rotor in order of 13.6% for a velocity of 10.4 m/s.

No description available.

The aim of this work is to study the in-vitro aerodynamic performance of a new inhaled theophylline formulation prepared by supercritical fluids technique. For the analysis of the output from the in-vitro tests (and further in-vivo tests) a new, fast, sensitive high performance liquid chromatographic (HPLC) method was developed and validated for the determination of theophylline and other related derivatives in aqueous and urine samples using new packing materials (monolithic columns). These columns achieve efficient separation under lower backpressure and shorter time comparing to other traditionally or newly introduced C18 columns. Solution enhanced dispersion by supercritical fluid (SEDS) process has been applied for the production of anhydrous theophylline as pure crystals in the range 2-5 ¿m to be used as new inhaled dry powder formulation for asthma. Fifteen theophylline samples have been prepared under different experimental conditions. The drug produced by this method has been subject to a number of solid-phase analytical procedures designed to establish the crystal structure [X-ray powder diffraction (XRPD)], the structure and conformation [(FTIR), Fourier-transform Raman spectroscopy (FT-Raman)], and the morphology and particle size [scanning electron microscope (SEM)]. While, thermal gravimetric analysis (TGA), and differential scanning calorimetry (DSC) have been used to monitor any phase transition or polymorphic changes after processing. All these analytical techniques gave a satisfactory indication of the solid-state chemistry of the processed particles and assess the development of new inhalation product. The performance of inhaled SEDS theophylline with or without a carrier was evaluated using the developed HPLC method. Three samples having different particle sizes were selected out of the prepared powders by SEDS technique to be tested. The dose sampling unit and the Anderson Cascade Impactor were used to determine the in-vitro emitted dose and the deposition profiles of SEDS samples, respectively. The effect of different inhalation flows was studied using two different flows 28.3, and 60 L min-1 with 4 L inhalation volume. Different DPI devices were investigated in this study; Easyhaler® and Spinhaler®. The particle size has an important effect on the aerodynamic behaviour and deposition profile of inhaled drug, the smaller the particles the greater the total lung deposition. The presence of a carrier improves the respirable fraction for all the tested formulations. / Egyptian Ministry of Higher Education

Reversible axial flow fans are used as emergency ventilation fans to discharge the smoke generated on the probable fires occurring in the underground transportation systems and mines as quickly as possible, without causing any harm to people exposed to it. The fans which are placed in different configurations according to the location of fire must be able to work bi-directionally, namely reversible. Due to this fact, the blade profiles of the fan must possess the same aerodynamic performance while working on either discharge or suction condition of the fan, dictated by direction of the rotation. This manuscript consists of the computation of the aerodynamic performances of symmetrical blade profiles of fully reversible axial fans by computational fluid mechanics (CFD) methods, developing a methodology for the design of reversible axial fans and analysis of the designed fan with CFD methods. The aerodynamic performances of the blade cascades are evaluated using FLUENT 6.0 software for different Reynolds numbers, solidities and angle of attacks of the cascade. The results of these computations are embedded into the developed methodology. Performance analysis of the reversible axial flow fan, which is designed with the developed methodology, is done with CFD techniques.

The modern trend of gas turbines design is towards lighter, highly efficient,and more compact engines. Such situation imposes on engineers to continuouslysearch for improved and optimum designs. The thesis presented aims at researching possible performance improvements regarding axial gapdistance in transonic compressors. Decreasing the axial gap would result inlighter engines and achieve design goals. The influence of decreasing the axialgap on performance and structure integrity should be throughly analyzed. This thesis work includes numerical investigations on the axial gap distance effect on performance efficiency and related unsteady aerodynamics phenomena. The first one and a half compressor stages of a Siemens Gas Turbine are modeled in ANSYS CFX. Different axial gap models are simulated for differentconfigurations. The steady state solution is obtained to be initialized for transient time marching calculations. Furthermore, the computational cost of transient calculations is reduced through a geometry scaling technique. The unsteady behavior is further analyzed by a Harmonic Balance solver implemented in STAR-CCM+ software, and compared to a reference case transient calculations. The results obtained supports the presence of an optimalaxial gap distance for maximum efficiency in transonic compressors. Further, the harmonic balance method shows good possibilities for cost and time reductions in transonic compressors performance calculations.

<p>This dissertation investigates the optimal aerodynamic performance and design of conventional and coaxial helicopters in hover and forward flight using conventional and higher harmonic blade pitch control. First, we describe a method for determining the blade geometry, azimuthal blade pitch inputs, optimal shaft angle (rotor angle of attack), and division of propulsive and lifting forces among the components that minimize the total power for a given forward flight condition. The optimal design problem is cast as a variational statement that is discretized using a vortex lattice wake to model inviscid forces, combined with two-dimensional drag polars to model profile losses. The resulting nonlinear constrained optimization problem is solved via Newton iteration. We investigate the optimal design of a compound vehicle in forward flight comprised of a coaxial rotor system, a propeller, and optionally, a fixed wing. We show that higher harmonic control substantially reduces required power, and that both rotor and propeller efficiencies play an important role in determining the optimal shaft angle, which in turn affects the optimal design of each component. Second, we present a variational approach for determining the optimal (minimum power) torque-balanced coaxial hovering rotor using Blade Element Momentum Theory including swirl. We show that the optimal hovering coaxial rotor generates only a small percentage of its total thrust on the portion of the lower rotor operating in the upper rotor's contracted wake, resulting in an optimal design with very different upper and lower rotor twist and chord distributions. We also show that the swirl component of induced velocity has a relatively small effect on rotor performance at the disk loadings typical of helicopter rotors. Third, we describe a more refined model of the wake of a hovering conventional or coaxial rotor. We approximate the rotor or coaxial rotors as actuator disks (though not necessarily uniformly loaded) and the wake as contracting cylindrical vortex sheets that we represent as discrete vortex rings. We assume the system is axisymmetric and steady in time, and solve for the wake position that results in all vortex sheets being aligned with the streamlines of the flow field via Newton iteration. We show that the singularity that occurs where the vortex sheet terminates at the edge of the actuator disk is resolved through the formation of a 45 degree logarithmic spiral in hover, which results in a non-uniform inflow, particularly near the edge of the disk where the flow is entirely reversed, as originally hypothesized by previous authors. We also quantify the mutual interference of coaxial actuator disks of various axial spacing. Finally, we combine our forward flight optimization procedure and the Blade Element Momentum Theory hover optimization to form a variational approach to the multipoint aerodynamic design optimization of conventional and coaxial helicopter rotors. The resulting nonlinear constrained optimization problem may be used to map the Pareto frontier, i.e., the set of rotor designs for which it is not possible to improve upon the performance in one flight condition without degrading performance in the other. We show that for both conventional and coaxial rotors analyzed in hover and high speed flight, a substantial tradeoff in performance must be made between the two flight conditions. Finally, computational results demonstrate that higher harmonic control is able to improve the Pareto efficiency for both conventional and coaxial rotors.</p> / Dissertation

Este trabalho apresenta a simulação numérica do escoamento turbulento em torno de uma turbina eólica de eixo vertical de pequeno porte, Savonius tipo helicoidal com torção de 180° nas pás. Com o intuito de avaliar a metodologia computacional empregada os resultados numéricos obtidos são comparados com os resultados experimental e numérico contidos no estado da arte. Também, compara-se o coeficiente de toque da turbina Savonius helicoidal com a turbina Savonius convencional. As simulações numéricas são baseadas no Método de Volumes Finitos, e para tal emprega-se o programa Fluent /Ansys versão 13.0 que resolve as equações da continuidade e as equações de Navier-Stokes com médias de Reynolds, juntamente com o modelo de turbulência . As simulações são desenvolvidas empregando diferentes malhas computacionais em estudos transientes, tridimensionais, com a turbina estacionária. A avaliação da qualidade da malha é realizada através do método de Índice de Convergência de Malha (GCI) o qual analisa o quão longe os resultados estão da solução assintótica para a malha utilizada. Após a análise da qualidade de malha, realizam-se simulações com a turbina em rotação as quais fazem uso da malha contendo uma região móvel possibilitando a imposição de uma velocidade angular ao rotor. O coeficiente de torque é obtido nas simulações e a partir dele calcula-se o coeficiente de potência. Além da análise do desempenho do rotor realiza-se uma análise qualitativa das características do escoamento sobre a turbina. A turbina Savonius helicoidal apresenta um valor de coeficiente de potência de 0,175 para a razão de velocidade de ponta de 0,58 considerando correção do efeito de bloqueio. Os resultados obtidos apresentam boa concordância com os resultados publicados por outros autores. / This dissertation presents the numerical simulation of the turbulent flow around of a small sized vertical axis wind turbine, consisting in a helical Savonius type with a 180° degree of blade twist. In order to evaluate the used methodology the obtained results are compared with the state of the art numerical and experimental data. It will be also presented the comparison between the torque coefficient of the conventional Savonius turbine and the helical Savonius turbine. The numerical simulations are based on the Finite Volume Method (FVM), using the commercial code Fluent/ANSYS version 13.0, which solves the continuity and Navier-Stokes through the Reynolds time-averaged methodology, including the turbulence model. The simulations are developed using different computational meshes for transient and three-dimensional studies with the stationary turbine. The evaluating the quality of the mesh is performed by of Grid Convergence Index (GCI) method which analyzes how far the results are the asymptotic solution to the mesh used. After the evaluation of the mesh quality, it was simulated a case considering the rotor motion using the moving mesh configuration, allowing the imposition of an angular velocity to the turbine. In the post-processing stage, it is possible to obtain the torque coefficient on the rotor shaft, allowing the calculation of the power coefficient for the turbine. In addition to the performance analysis, it is also made a qualitative analysis of the flow characteristics over the turbine rotor and in both cases presenting a good correspondence with the results in the literature. The helical Savonius turbine presents a value of power coefficient of 0.175 to a tip speed ratio of 0.58 whereas blocking effect correction.