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Yes / This study focuses on numerical modeling of condensation of water vapor in a Laval nozzle, using the liquid drop nucleation theory. Influence of nozzle geometry, pressure, and temperature on the average drop size is reported. A computer program written in MATLAB was used used to calculate the nucleation and condensation of water vapor in the nozzle. The simulation results are validated with the available experimental data in the literature for steam condensation. The model reveals that the average drop size is reduced by increasing the divergent angle of the nozzle. The results also confirm that increasing the inlet pressure has a direct effect on the average drop size while temperature rise has an inverse effect on the drop size.

No / Nucleation and condensation of mercury vapor has been investigated in various divergent angle and operating condition. Divergent angle has a great effect on droplet size at the end of nozzle. Influence of operating condition such as pressure and temperature on the size of droplet has been investigated. A one-dimensional mathematical model based on classical nucleation and growth has been developed to calculate the nucleation and condensation of mercury vapor. A mercury vapour turbine has been used in conjunction with a steam turbine for generating electricity. The mercury cycle offers an efficiency increase compared to a steam-only cycle because energy can be injected into the Rankine Cycle at higher temperature. The target of modeling is predicting the droplet size of mercury nano-particles during rapid expansion. The results are verified by accurate experimental data available in the literature. The governing equations were solved using Runge-Kutta third-order numerical method in MATLAB software.

There has been, and will continue to be, tremendous growth in the use and distribution of liquefied natural gas (LNG). As LNG poses the hazard of flammable vapor cloud formation from a release, which may result in a massive fire, increased public concerns have been expressed regarding the safety of this fuel. In addition, regulatory authorities in the U.S. as well as all over the world expect the implementation of consequence mitigation measures for LNG spills. For the effective and safer use any safety measure to prevent and mitigate an accidental release of LNG, it is critical to understand thoroughly the action mechanisms. Water spray curtains are generally used by petro-chemical industries to prevent and mitigate heavier-than-air toxic or flammable vapors. It is also used to cool and protect equipment from heat radiation of fuel fires. Currently, water spray curtains are recognized as one of the economic and promising techniques to enhance the dispersion of the LNG vapor cloud formed from a spill. Usually, water curtains are considered to absorb, dilute, disperse and warm a heavier-than-air vapor cloud. Dispersion of cryogenic LNG vapor behaves differently from other dense gases because of low molecular weight and extremely low temperature. So the interaction between water curtain and LNG vapor is different than other heavier vapor clouds. Only two major experimental investigations with water curtains in dispersing LNG vapor clouds were undertaken during the 1970s and 1980s. Studies showed that water spray curtains enhanced LNG vapor dispersion from small spills. However, the dominant phenomena to apply the water curtain most effectively in controlling LNG vapor were not clearly demonstrated. The main objective of this research is to investigate the effectiveness of water spray curtains in controlling the LNG vapor clouds from outdoor experiments. A research methodology has been developed to study the dispersion phenomena of LNG vapor by the action of different water curtains experimentally. This dissertation details the research and experiment development. Small scale outdoor LNG spill experiments have been performed at the Brayton Fire Training Field at Texas A&M University. Field test results regarding important phenomena are presented and discussed. Results have determined that the water curtains are able to reduce the concentration of the LNG vapor cloud, push the vapor cloud upward and transfer heat to the cloud. These are being identified due to the water curtain mechanisms of entrainment of air, dilution of vapor with entrained air, transfer of momentum and heat to the gas cloud. Some of the dominant actions required to control and disperse LNG vapor cloud are also identified from the experimental tests. The gaps are presented as the future work and recommendation on how to improve the experiments in the future. This will benefit LNG industries to enhance its safety system and to make LNG facilities safer.

Orientador: Ulisses Rocha Antuniassi / Banca: Otavio Jorge Grigoli Abi Saab / Banca: Marco Antonio Gandolfo / Resumo: O presente trabalho teve por objetivo verificar a interferência de adjuvantes na quantidade de ar incluído em gotas geradas por pontas com indução de ar, bem como avaliar o espectro resultante destas condições de pulverização. Para o estudo foram utilizadas nove caldas, sendo uma composta apenas por água e oito soluções contendo adjuvantes (óleo mineral, óleo vegetal, mistura de lecitina e ácido propiônico, nonil fenoxi poli etanol, dois adjuvantes a base de nonil fenol etoxilado, copolímero de poliéster e silicone, e lauril éter sulfato de sódio) e três pontas de pulverização jato plano, sendo duas com indução de ar (Air Guardian e Ultra Lo-Drift - Hypro) e uma com pré-orifício (Drift Guard - Spray Systems). O estudo foi realizado em duas etapas, sendo elas a quantificação do ar incluído nas gotas de pulverização e a análise do espectro produzido. O ar incluído foi calculado através da diferença de volume da mistura pulverizada (ar mais líquido) e apenas do líquido, que foi feito por meio de coletas de amostras de pulverização em uma proveta graduada. A determinação do espectro de gotas foi realizada por um analisador de tamanho de partículas por difração de raios laser Mastersizer S (Malvern Instruments). Para análise estatística os valores das variáveis do espectro de gotas e % ar incluído para os diferentes adjuvantes e pontas foram comparados pelo Intervalo de Confiança para Diferenças entre as Médias a 5 % de probabilidade (IC95%). Também foram feitas as correlações entre as diferentes variáveis através do coeficiente de Pearson a 5% de probabilidade. As análises do espectro de gotas demonstraram diferenças entre os adjuvantes, assim como diferenças de comportamento dos adjuvantes de acordo com o tipo de ponta. Todos os adjuvantes ocasionaram o aumento do percentual de ar incluído nas gotas em relação à água, observando... (Resumo completo, clicar acesso eletrônico abaixo) / Abstract: This study aimed to verify the influence of adjuvants on the amount of air included in droplets generated by spray nozzles with air induction, as well as to evaluate the droplet spectrum generated in these conditions. For the study, it were used nine spray solutions, one including only water and eight containing adjuvants (mineral oil, vegetable oil, a mixture of lecithin and propionic acid, nonyl phenoxy poly ethanol, the two adjuvants based on nonyl phenol ethoxylate based, copolymer polyester and silicon, and sodium lauryl ether sulfate) and three flat fan spray nozzles, including two air induction (Air Guardian and Ultra Lo-Drift - Hypro) and a pre orifice (Drift Guardian - Spray Systems). The study was conducted in two steps: the quantification of air included in the spray droplets and the droplet spectrum produced. The amount of air included was calculated by the difference in volume of the solution after praying (liquid plus air) and only the solution (before spraying), which was done by collecting samples of the solutions in a graduated cylinder. The determination of the droplet spectrum was carried out by a particle size analyzer by laser device Mastersizer S (Malvern Instruments). Data collected for the variables of droplet spectrum and air included with different adjuvants and nozzles were subjected to statistical analysis by the calculation of the Confidence Interval at 95% (CI95%). Correlations between different variables were calculated by Pearson's correlation at 5% probability. The analysis of the droplet spectrum showed differences between the different adjuvants, as well as differences in the behavior of adjuvants according to the type of nozzle. All adjuvant caused an increase in the percentage of air included compared to the water, in which some different behaviors were observed for each nozzle. Looking at the relations between the variables... (Complete abstract click electronic access below) / Mestre

Made available in DSpace on 2014-06-11T19:24:39Z (GMT). No. of bitstreams: 0 Previous issue date: 2011-02-08Bitstream added on 2014-06-13T20:31:53Z : No. of bitstreams: 1 mota_aab_me_botfca.pdf: 2185132 bytes, checksum: bc81471882e24fbbd82fb00386fab303 (MD5) / Conselho Nacional de Desenvolvimento Científico e Tecnológico (CNPq) / O presente trabalho teve por objetivo verificar a interferência de adjuvantes na quantidade de ar incluído em gotas geradas por pontas com indução de ar, bem como avaliar o espectro resultante destas condições de pulverização. Para o estudo foram utilizadas nove caldas, sendo uma composta apenas por água e oito soluções contendo adjuvantes (óleo mineral, óleo vegetal, mistura de lecitina e ácido propiônico, nonil fenoxi poli etanol, dois adjuvantes a base de nonil fenol etoxilado, copolímero de poliéster e silicone, e lauril éter sulfato de sódio) e três pontas de pulverização jato plano, sendo duas com indução de ar (Air Guardian e Ultra Lo-Drift – Hypro) e uma com pré-orifício (Drift Guard – Spray Systems). O estudo foi realizado em duas etapas, sendo elas a quantificação do ar incluído nas gotas de pulverização e a análise do espectro produzido. O ar incluído foi calculado através da diferença de volume da mistura pulverizada (ar mais líquido) e apenas do líquido, que foi feito por meio de coletas de amostras de pulverização em uma proveta graduada. A determinação do espectro de gotas foi realizada por um analisador de tamanho de partículas por difração de raios laser Mastersizer S (Malvern Instruments). Para análise estatística os valores das variáveis do espectro de gotas e % ar incluído para os diferentes adjuvantes e pontas foram comparados pelo Intervalo de Confiança para Diferenças entre as Médias a 5 % de probabilidade (IC95%). Também foram feitas as correlações entre as diferentes variáveis através do coeficiente de Pearson a 5% de probabilidade. As análises do espectro de gotas demonstraram diferenças entre os adjuvantes, assim como diferenças de comportamento dos adjuvantes de acordo com o tipo de ponta. Todos os adjuvantes ocasionaram o aumento do percentual de ar incluído nas gotas em relação à água, observando... / This study aimed to verify the influence of adjuvants on the amount of air included in droplets generated by spray nozzles with air induction, as well as to evaluate the droplet spectrum generated in these conditions. For the study, it were used nine spray solutions, one including only water and eight containing adjuvants (mineral oil, vegetable oil, a mixture of lecithin and propionic acid, nonyl phenoxy poly ethanol, the two adjuvants based on nonyl phenol ethoxylate based, copolymer polyester and silicon, and sodium lauryl ether sulfate) and three flat fan spray nozzles, including two air induction (Air Guardian and Ultra Lo-Drift - Hypro) and a pre orifice (Drift Guardian - Spray Systems). The study was conducted in two steps: the quantification of air included in the spray droplets and the droplet spectrum produced. The amount of air included was calculated by the difference in volume of the solution after praying (liquid plus air) and only the solution (before spraying), which was done by collecting samples of the solutions in a graduated cylinder. The determination of the droplet spectrum was carried out by a particle size analyzer by laser device Mastersizer S (Malvern Instruments). Data collected for the variables of droplet spectrum and air included with different adjuvants and nozzles were subjected to statistical analysis by the calculation of the Confidence Interval at 95% (CI95%). Correlations between different variables were calculated by Pearson's correlation at 5% probability. The analysis of the droplet spectrum showed differences between the different adjuvants, as well as differences in the behavior of adjuvants according to the type of nozzle. All adjuvant caused an increase in the percentage of air included compared to the water, in which some different behaviors were observed for each nozzle. Looking at the relations between the variables... (Complete abstract click electronic access below)

The first part of this work focuses on control experiments performed on an unstable kerosene-fueled turbulent combustor. Using a phase shift controller and primary fuel modulation stability is successfully gained for a wide band of global equivalence ratios allowing the limitations of the control scheme to be characterized. It is shown that control signal saturation can significantly impact the ability of the control scheme to stabilize the system. Three different regions of controllability are defined based on the degree of saturation. A hysteresis behavior is also found to exist for the controller settings depending on whether stability is being maintained or realized for an unstable system. The second part of this work focuses on the impact that primary fuel modulation has on the fuel spray. Measurements for a simplex nozzle and an air-assist nozzle are taken under both static and dynamic operating conditions with a Phase Doppler Anemometry system. The dynamic modulation is found to significantly impact the spray properties of both nozzles. / Master of Science

Plug nozzle, a passive altitude adaptive nozzle, for futuristic SSTO applications, exhibits greater efficiency as compared to conventional nozzles over a wide range of altitudes. The plug nozzle comprises of a primary nozzle and a contoured plug; an under–expanded jet exiting the primary nozzle is allowed to further expand over the plug surface for altitude adaptation. At design condition the flow expands correctly to the ambient conditions on the full length plug surface, while at off design conditions the flow adapts to the ambient conditions through wave interactions within the nozzle core jet. Based on thrust to weight considerations, the full length plug is truncated and this results in a base flow rich in flow physics. In addition, the base flow exhibits an interesting transitional behaviour from open wake to a closed wake because of the wave interactions within the nozzle core jet. The plug surface flow can further exhibit flow complexities because of wave interactions resulting from the shear layer emanating from the splitter plates, in case of clustered plug flows. Considering these flow complexities, the design of the plug nozzles and analysing the associated flows can be a challenge to the aerodynamic community. An attempt has been made in understanding this class of flows in this thesis. This objective has been accomplished using both experimental and computational tools. In the present work, both the linear and annular plug nozzle geometries have been analysed for a wide range of pressure ratios spanning from 5to 80. The linear and annular nozzles have been designed for similar flow conditions and their respective design pressure ratios are 60and 66. From the experimental and computational results, it has been shown that the computational solver performs well in predicting the wave interactions on the plug surface. In addition the limitations of the computational solver in predicting the plug base flows in general has been brought out. This limitation in itself need not be considered as a serious handicap in the design and analysis of plug nozzle flows; this is because the plug base contribution to the thrust is very minimal, as has been brought out in this thesis. Apart from this the high quality experimental data generated is also of immense value to the CFD community as this also serves as a valuable data base for CFD code validation. For analysis, the plug flow field has been categorized into three different regimes based on the primary nozzle lip expansion fan extent. The flow field is categorised based on the reflection of the primary nozzle lip expansion fan from plug surface, base region shear layer and symmetry line downstream of the base region recirculation bubble. This flow division is particularly helpful in understanding the base wake characteristics with increasing pressure ratio. The base lip pressure and the base pressure variation have been discussed with respect to the primary nozzle lip expansion fan extent. In the open wake regime (or for low pressure ratios) the wave interactions within the core jet flow impinge on the base region shear layer. Because of these interactions it is difficult to propose an empirical model for open wake base pressure. In the closed wake regime (for higher pressure ratios), the base region recirculation bubble is completely under the shower of primary nozzle lip expansion fan. Hence the base lip pressure and base pressure are frozen with respect to stagnation conditions. Based on these insights it was possible to propose empirical models for linear and annular closed wake base pressure. Along with these, a mathematical model defining a reference pressure ratio PR∗, beyond which the closed wake base pressure is expected to be more than the ambient pressure has also been proposed. This is expected to serve as a good design parameter. In case of linear plug flows, this also serves the purpose of base wake transition, for the cases considered in this thesis. The flow expansion process or the primary nozzle lip expansion fan extent was also useful in understanding the differences between the linear and annular plug nozzle flow fields. In a linear plug nozzle, the flow expands only in the streamwise direction while in an annular plug nozzle the flow expands both along the streamwise and azimuthal directions. The flow expands at a faster rate in case of annular nozzle as against linear nozzle. Hence differences are observed between the linear and annular nozzle on plug and base surfaces. On the annular plug surface more wave interactions are observed because of faster expansion. With regard to base characteristics, faster expansion in annular plug nozzle, with respect to linear nozzle, results in a lower base lip pressure, lower base pressure and higher wake transition pressure ratio. The realistic cluster plug configurations have also been considered for the present studies. The effects of clustering on the plug nozzle flow field have been brought out by considering two different linear cluster nozzles and one annular cluster nozzle. The differences in the flow field of a simple and cluster plug nozzle has been discussed. In case of simple plug nozzle wave interactions are observed only in the stream wise direction, while in case of cluster plug nozzle three dimensional wave interactions are observed because of the splitter plates. Along the splitter plate differential end conditions introduce a curved recompression shock on the plug surface. This recompression shock in turn induces a streamwise vortex and also a secondary shock. It has been observed that differences between the simple and cluster plug surface pressure field are because of three dimensional wave interactions. Regarding the base pressure, differences between the simple and cluster geometries were observed for shorter truncation plug lengths (20% length plug). While for longer plug lengths (more than 34% length) the effects of clustering were reduced on the base pressure. Regarding the transition pressure ratio, differences were observed between simple and clustered plug nozzles for all the plug lengths considered. In addition, the performance of the plug nozzles has been carried out. From the analysis it was found that the primary nozzle and plug surface are major contributors towards thrust. The base surface contributes only about 2– 3% of the thrust at design condition. Hence, from a design point of view, a computational solver can be a useful tool considering its efficacy on the plug surface and in the primary nozzle.

Plug nozzle, a passive altitude adaptive nozzle, for futuristic SSTO applications, exhibits greater efficiency as compared to conventional nozzles over a wide range of altitudes. The plug nozzle comprises of a primary nozzle and a contoured plug; an under–expanded jet exiting the primary nozzle is allowed to further expand over the plug surface for altitude adaptation. At design condition the flow expands correctly to the ambient conditions on the full length plug surface, while at off design conditions the flow adapts to the ambient conditions through wave interactions within the nozzle core jet. Based on thrust to weight considerations, the full length plug is truncated and this results in a base flow rich in flow physics. In addition, the base flow exhibits an interesting transitional behaviour from open wake to a closed wake because of the wave interactions within the nozzle core jet. The plug surface flow can further exhibit flow complexities because of wave interactions resulting from the shear layer emanating from the splitter plates, in case of clustered plug flows. Considering these flow complexities, the design of the plug nozzles and analysing the associated flows can be a challenge to the aerodynamic community. An attempt has been made in understanding this class of flows in this thesis. This objective has been accomplished using both experimental and computational tools. In the present work, both the linear and annular plug nozzle geometries have been analysed for a wide range of pressure ratios spanning from 5to 80. The linear and annular nozzles have been designed for similar flow conditions and their respective design pressure ratios are 60and 66. From the experimental and computational results, it has been shown that the computational solver performs well in predicting the wave interactions on the plug surface. In addition the limitations of the computational solver in predicting the plug base flows in general has been brought out. This limitation in itself need not be considered as a serious handicap in the design and analysis of plug nozzle flows; this is because the plug base contribution to the thrust is very minimal, as has been brought out in this thesis. Apart from this the high quality experimental data generated is also of immense value to the CFD community as this also serves as a valuable data base for CFD code validation. For analysis, the plug flow field has been categorized into three different regimes based on the primary nozzle lip expansion fan extent. The flow field is categorised based on the reflection of the primary nozzle lip expansion fan from plug surface, base region shear layer and symmetry line downstream of the base region recirculation bubble. This flow division is particularly helpful in understanding the base wake characteristics with increasing pressure ratio. The base lip pressure and the base pressure variation have been discussed with respect to the primary nozzle lip expansion fan extent. In the open wake regime (or for low pressure ratios) the wave interactions within the core jet flow impinge on the base region shear layer. Because of these interactions it is difficult to propose an empirical model for open wake base pressure. In the closed wake regime (for higher pressure ratios), the base region recirculation bubble is completely under the shower of primary nozzle lip expansion fan. Hence the base lip pressure and base pressure are frozen with respect to stagnation conditions. Based on these insights it was possible to propose empirical models for linear and annular closed wake base pressure. Along with these, a mathematical model defining a reference pressure ratio PR∗, beyond which the closed wake base pressure is expected to be more than the ambient pressure has also been proposed. This is expected to serve as a good design parameter. In case of linear plug flows, this also serves the purpose of base wake transition, for the cases considered in this thesis. The flow expansion process or the primary nozzle lip expansion fan extent was also useful in understanding the differences between the linear and annular plug nozzle flow fields. In a linear plug nozzle, the flow expands only in the streamwise direction while in an annular plug nozzle the flow expands both along the streamwise and azimuthal directions. The flow expands at a faster rate in case of annular nozzle as against linear nozzle. Hence differences are observed between the linear and annular nozzle on plug and base surfaces. On the annular plug surface more wave interactions are observed because of faster expansion. With regard to base characteristics, faster expansion in annular plug nozzle, with respect to linear nozzle, results in a lower base lip pressure, lower base pressure and higher wake transition pressure ratio. The realistic cluster plug configurations have also been considered for the present studies. The effects of clustering on the plug nozzle flow field have been brought out by considering two different linear cluster nozzles and one annular cluster nozzle. The differences in the flow field of a simple and cluster plug nozzle has been discussed. In case of simple plug nozzle wave interactions are observed only in the stream wise direction, while in case of cluster plug nozzle three dimensional wave interactions are observed because of the splitter plates. Along the splitter plate differential end conditions introduce a curved recompression shock on the plug surface. This recompression shock in turn induces a streamwise vortex and also a secondary shock. It has been observed that differences between the simple and cluster plug surface pressure field are because of three dimensional wave interactions. Regarding the base pressure, differences between the simple and cluster geometries were observed for shorter truncation plug lengths (20% length plug). While for longer plug lengths (more than 34% length) the effects of clustering were reduced on the base pressure. Regarding the transition pressure ratio, differences were observed between simple and clustered plug nozzles for all the plug lengths considered. In addition, the performance of the plug nozzles has been carried out. From the analysis it was found that the primary nozzle and plug surface are major contributors towards thrust. The base surface contributes only about 2– 3% of the thrust at design condition. Hence, from a design point of view, a computational solver can be a useful tool considering its efficacy on the plug surface and in the primary nozzle.