Dans le cycle de vie logiciel nous avons principalement les activités (1) de pré-développement (l'analyse des besoins, les spécifications, la conception architecturale et la conception détaillée), (2) de développement (l'implémentation, le prototypage, les tests unitaires et les tests d'intégration) et (3) de post-développement (déploiement). Le déploiement de logiciel couvre l'ensemble des activités post-développement. Les activités de déploiement permettent de rendre une application utilisable. Elles sont identifiées comme cycle de vie de déploiement couvrant l'archivage des logiciels, leur chargement, leur installation sur les sites clients, leur configuration, leur activation ainsi que leur mise à jour. Le développement de systèmes à composants a permis de mieux identifier cette partie du cycle de vie global du logiciel, comme le montrent de nombreux travaux industriels et académiques. Cependant ces travaux sont en général développés de manière ad' hoc, spécifiques à une plate-forme donnée. Peu flexibles, ils s'adaptent difficilement aux stratégies des entreprises. Les systèmes de déploiement comme le montrent ceux supportés par les environnements de type intergiciel CCM, .Net, EJB développent de manière spécifique les mécanismes et outils de déploiement et introduisent des choix prédéfinis et figés de stratégies de déploiement. Nos travaux se situent dans le contexte de logiciels à base de composants distribués et portent sur la proposition d'un environnement générique pour supporter leur déploiement. C'est une nouvelle génération de systèmes proposée essentiellement par le monde académique de génie logiciel qui s'est approprié la problématique de déploiement à large échelle. Dans ce contexte, nous proposons une approche basée sur l'ingénierie dirigée par les modèles où nous introduisons les abstractions nécessaires pour décrire les logiciels à déployer, les infrastructures de déploiement, les stratégies de déploiement ainsi que le processus de déploiement avec l'identification et l'ordonnancement des activités à accomplir et le support pour leur exécution.

Este trabalho apresenta o resultado da aplicação do Método dos Volumes Finitos, adotado pelo software comercial Star-CCM+ na simulação para o regime permanente de escoamentos turbulentos incompressíveis e compressíveis sobre seções de aerofólios. Para o caso incompressível modelam-se seções do aerofólio NACA 0012 com ângulo de ataque zero. Para o caso compressível, uma seção do aerofólio supercrítico OAT15A em pequeno ângulo de ataque é modelada. Os domínios computacionais são discretizados por malhas não estruturadas de células poliédricas ou por malhas estruturadas de geração hiperbólica para diferentes topologias e parâmetros construtivos determinados pela estimativa de grandezas do fenômeno físico, como a altura da primeira camada de células quadrilaterais junto à parede. A qualidade e adequação dessas malhas para as simulações são verificadas por estudo de dependência quanto ao nível de refinamento e também quanto à posição do contorno onde o escoamento é livre no caso de escoamento compressível. Na metodologia de verificação, o índice de convergência de malha GCI e a ordem observada de convergência do método (dos Volumes Finitos) são obtidos para três níveis de refinamento com o propósito de selecionar uma malha de trabalho que concilie precisão e esforço computacional com os recursos disponíveis. As simulações são conduzidas para dois modelos de turbulência – o modelo Spalart-Allmaras e o modelo k-ω/SST. Os resultados obtidos pela aplicação desses modelos são interpretados sob o ponto de vista fenomenológico e comparados com os resultados experimentais disponíveis em literatura. / The Finite Volumes Method adopted by the commercial software Star-CCM+ is applied to the simulation of the steady state regime of incompressible and compressible turbulent flows over selected airfoil’s sections. The physical model used with the incompressible flow case is a NACA 0012 airfoil section at zero angle of attack. The ONERA’s OAT15A supercritical airfoil section at small angle of attack applies to the compressible flow case. The computational domains are discretized by structured and unstructured meshes for different topologies and far field configurations. The structured meshes are of the quadrilateral type with hyperbolic node distribution whilst the unstructured meshes use polyhedral cells. The grids are generated by applying a methodology where estimates of the flow variables are used as input for the grid’s constructive parameters like the near wall cell thickness. Grid dependency studies are carried out in order to verify the grid’s quality and suitability to represent the physical phenomena. The grid’s asymptotic convergence index GCI and its observed order of convergence are evaluated for three refinement levels and far field position for the compressible flow cases. The objective is to select the most suitable grid taking into account the accuracy requirements and the computational resources available. The one-equation Spalart-Allmaras turbulence model and the two-equation k-ω/SST turbulence models are used. The numerical results are discussed from the physical point of view and compared with the experimental ones available in literature.

Este trabalho apresenta o resultado da aplicação do Método dos Volumes Finitos, adotado pelo software comercial Star-CCM+ na simulação para o regime permanente de escoamentos turbulentos incompressíveis e compressíveis sobre seções de aerofólios. Para o caso incompressível modelam-se seções do aerofólio NACA 0012 com ângulo de ataque zero. Para o caso compressível, uma seção do aerofólio supercrítico OAT15A em pequeno ângulo de ataque é modelada. Os domínios computacionais são discretizados por malhas não estruturadas de células poliédricas ou por malhas estruturadas de geração hiperbólica para diferentes topologias e parâmetros construtivos determinados pela estimativa de grandezas do fenômeno físico, como a altura da primeira camada de células quadrilaterais junto à parede. A qualidade e adequação dessas malhas para as simulações são verificadas por estudo de dependência quanto ao nível de refinamento e também quanto à posição do contorno onde o escoamento é livre no caso de escoamento compressível. Na metodologia de verificação, o índice de convergência de malha GCI e a ordem observada de convergência do método (dos Volumes Finitos) são obtidos para três níveis de refinamento com o propósito de selecionar uma malha de trabalho que concilie precisão e esforço computacional com os recursos disponíveis. As simulações são conduzidas para dois modelos de turbulência – o modelo Spalart-Allmaras e o modelo k-ω/SST. Os resultados obtidos pela aplicação desses modelos são interpretados sob o ponto de vista fenomenológico e comparados com os resultados experimentais disponíveis em literatura. / The Finite Volumes Method adopted by the commercial software Star-CCM+ is applied to the simulation of the steady state regime of incompressible and compressible turbulent flows over selected airfoil’s sections. The physical model used with the incompressible flow case is a NACA 0012 airfoil section at zero angle of attack. The ONERA’s OAT15A supercritical airfoil section at small angle of attack applies to the compressible flow case. The computational domains are discretized by structured and unstructured meshes for different topologies and far field configurations. The structured meshes are of the quadrilateral type with hyperbolic node distribution whilst the unstructured meshes use polyhedral cells. The grids are generated by applying a methodology where estimates of the flow variables are used as input for the grid’s constructive parameters like the near wall cell thickness. Grid dependency studies are carried out in order to verify the grid’s quality and suitability to represent the physical phenomena. The grid’s asymptotic convergence index GCI and its observed order of convergence are evaluated for three refinement levels and far field position for the compressible flow cases. The objective is to select the most suitable grid taking into account the accuracy requirements and the computational resources available. The one-equation Spalart-Allmaras turbulence model and the two-equation k-ω/SST turbulence models are used. The numerical results are discussed from the physical point of view and compared with the experimental ones available in literature.

Este trabalho apresenta o resultado da aplicação do Método dos Volumes Finitos, adotado pelo software comercial Star-CCM+ na simulação para o regime permanente de escoamentos turbulentos incompressíveis e compressíveis sobre seções de aerofólios. Para o caso incompressível modelam-se seções do aerofólio NACA 0012 com ângulo de ataque zero. Para o caso compressível, uma seção do aerofólio supercrítico OAT15A em pequeno ângulo de ataque é modelada. Os domínios computacionais são discretizados por malhas não estruturadas de células poliédricas ou por malhas estruturadas de geração hiperbólica para diferentes topologias e parâmetros construtivos determinados pela estimativa de grandezas do fenômeno físico, como a altura da primeira camada de células quadrilaterais junto à parede. A qualidade e adequação dessas malhas para as simulações são verificadas por estudo de dependência quanto ao nível de refinamento e também quanto à posição do contorno onde o escoamento é livre no caso de escoamento compressível. Na metodologia de verificação, o índice de convergência de malha GCI e a ordem observada de convergência do método (dos Volumes Finitos) são obtidos para três níveis de refinamento com o propósito de selecionar uma malha de trabalho que concilie precisão e esforço computacional com os recursos disponíveis. As simulações são conduzidas para dois modelos de turbulência – o modelo Spalart-Allmaras e o modelo k-ω/SST. Os resultados obtidos pela aplicação desses modelos são interpretados sob o ponto de vista fenomenológico e comparados com os resultados experimentais disponíveis em literatura. / The Finite Volumes Method adopted by the commercial software Star-CCM+ is applied to the simulation of the steady state regime of incompressible and compressible turbulent flows over selected airfoil’s sections. The physical model used with the incompressible flow case is a NACA 0012 airfoil section at zero angle of attack. The ONERA’s OAT15A supercritical airfoil section at small angle of attack applies to the compressible flow case. The computational domains are discretized by structured and unstructured meshes for different topologies and far field configurations. The structured meshes are of the quadrilateral type with hyperbolic node distribution whilst the unstructured meshes use polyhedral cells. The grids are generated by applying a methodology where estimates of the flow variables are used as input for the grid’s constructive parameters like the near wall cell thickness. Grid dependency studies are carried out in order to verify the grid’s quality and suitability to represent the physical phenomena. The grid’s asymptotic convergence index GCI and its observed order of convergence are evaluated for three refinement levels and far field position for the compressible flow cases. The objective is to select the most suitable grid taking into account the accuracy requirements and the computational resources available. The one-equation Spalart-Allmaras turbulence model and the two-equation k-ω/SST turbulence models are used. The numerical results are discussed from the physical point of view and compared with the experimental ones available in literature.

La evidente generalización durante los últimos años del uso de turbocompresores en motores de combustión interna ha sido debida a un aumento necesario de la concienciación sobre las emisiones contaminantes y sus efectos sobre el medio ambiente y las personas. Las normativas sobre emisiones contaminantes se han endurecido, generalizando el uso de técnicas como la Recirculación de Gases de Escape de Ruta Larga bajo unas condiciones de operación más amplias, con una mayor tasa e incluso bajo condiciones ambiente frías, lo que ha generado potenciales problemas de condensación de agua y daño en el compresor. Además, la tendencia actual de reducir el tamaño del motor para reducir el consumo, llamada " downsizing", ha provocado que el compresor tenga que funcionar muy cerca del límite de bombeo, lo que ha provocado, junto al descrito aumento de recirculación de gases de escape, una mayor exigencia en cuanto a durabilidad y funcionalidad del mismo. Los problemas comentados están claramente condicionados por la configuración geométrica de la entrada del compresor, ya sea por la condensación causada por los gases de escape al ser mezclados con aire fresco o por la influencia sobre el límite de bombeo y el resto de prestaciones. En este trabajo se propone un modelo de predicción de condensación para ser integrado en un código comercial de mecánica de fluidos computacional (STAR-CCM+). Dicho modelo se plantea de forma que aumente en la menor medida posible el coste computacional, asumiendo ciertas limitaciones como la ausencia de caracterización de las gotas de agua. Una vez implementado, se contrastan los resultados frente a datos experimentales de ensayos de durabilidad: se correlacionan las predicciones del modelo frente al impacto de la condensación sobre el rodete del compresor en diferentes configuraciones geométricas y condiciones de operación. Posteriormente se estudia el impacto del propio compresor sobre el proceso de mezcla y la condensación, lo que permite después desacoplar el problema y reducir en dos órdenes de magnitud el tiempo de cálculo al poder obviar la simulación del compresor. En cuanto a la influencia de la geometría en el margen de bombeo y resto de parámetros, se proponen varias geometrías sencillas y se analiza su impacto. Primero, se realizan ensayos experimentales en banco motor, tanto estacionarios para medir rendimiento y ruido como transitorios para definir el bombeo. Después, se ejecutan simulaciones CFD y se estudian los fenómenos locales que aparecen, en los que se evidencia una sensibilidad elevada de la geometría sobre el margen de bombeo y el resto de parámetros. Se puede destacar el desempeño de la geometría de entrada cónica, que produce un aumento considerable del margen de bombeo sin repercusiones en el resto de condiciones de operación; y la tobera convergente-divergente, que aumenta el margen de bombeo pero, además, también aumenta ligeramente el rendimiento en el resto del mapa del compresor, aunque a costa de reducir moderadamente las prestaciones a alto gasto másico. / Popularization of turbochargers in internal combustion engines has been produced in the recent years due to a needful increase of awareness of pollutant emissions and their repercussion on the environment and the population. Pollutant emission regulations have tightened, causing techniques such Long Route Exhaust Gas Recirculation to operate under a wider range of operating conditions, with higher rates and even under very cold ambient conditions, which generates a potential problem of water condensation and compressor damaging. Additionally, the actual trend consisting in reducing the size of the engine to reduce fuel consumption, known as "downsizing", has caused the compressor to have to work close to the surge limit. Together with the aforementioned extension of LR-EGR usage range, these phenomena have induced an increase of the compressor design requirements, concerning durability and functionality. Both problems are governed by the geometrical configuration of the compressor inlet and can be, then, studied accordingly. In this work, a predictive condensation model is proposed for being embedded in a computational fluid dynamics commercial code (STAR-CCM+). To allow a potential optimization of a given geometry, the model should introduce as low additional computational effort as possible, assuming certain limitations, though. For example, the characterization of water droplets is neglected. Once the model is implemented and verified, the results are compared with experimental data obtained from durability tests performed to assess the erosion of the compressor wheel under condensation generated by different LR-EGR T-joint configurations and operating conditions. After, the influence of the compressor on the mixing process and generation of condensates is addressed, proving that the simulation of the compressor can be decoupled from the T-joint numerical domain and reducing by two orders of magnitude the simulation time. Concerning the impact of the inlet geometry on the surge margin and the other important compressor parameters, several simple geometries are proposed, and their influence is assessed. First, experimental tests performed on an engine test bench are carried out: steady measurements for obtaining efficiency and noise emission and transient tests for characterizing the surge limit. Then, 3D-CFD simulations are performed using similar geometries, studying the local phenomena that appear and proving thus the sensitivity of the inlet geometry to the surge margin and the performance of the compressor. It may be highlighted the performance of the tapered duct, that produces a considerable positive shift of the surge margin without worsening the rest of the parameters and the convergent-divergent nozzle, which in addition to considerably improving the surge margin also enhances the isentropic efficiency of the compressor at low and mid mass flow rates. Nevertheless, the throat becomes a drawback at high mass flow rates, decreasing the compression ratio and efficiency under such conditions. / L'evident generalització durant els últims anys de l'ús de turbocompressors en motors de combustió interna ha estat deguda a un augment necessari de la conscienciació sobre les emissions contaminants i els seus efectes sobre el medi ambient i les persones. Les normatives sobre emissions contaminants s'han fet més restrictives, generalitzant l'ús de tècniques com la Recirculació de Gasos d'Escap de Ruta Llarga sota unes condicions d'operació més àmplies, amb una major taxa i fins i tot sota condicions ambient fredes, fet que ha generat potencials problemes de condensació d'aigua i danys al compressor. A més, la tendència actual de reduir la grandària del motor per millorar el consum, anomenada " downsizing", ha provocat que el compressor haja de funcionar molt a prop del límit de bombeig, fet que ha provocat, junt amb el descrit augment de recirculació de gasos d'escap, una major exigència quant a la seua durabilitat i funcionament. Els problemes esmentats estan clarament condicionats per la configuració geomètrica de l'entrada del compressor, ja siga per la condensació causada pels gasos d'escap al ser barrejats amb aire fresc o per la influència sobre el límit de bombeig i la resta de prestacions. En aquest treball es proposa un model de predicció de condensació per a ser integrat en un codi comercial de mecànica de fluids computacional (STAR-CCM+). Dit model es planteja de manera que augmente en la menor mesura possible el cost computacional, assumint certes limitacions com l'absència de caracterització de les gotes d'aigua. Una vegada implementat, es contrasten els resultats enfront de dades experimentals d'assajos de durabilitat: correlacionen les prediccions del model enfront de l'impacte de la condensació sobre el rodet del compressor en diferents configuracions geomètriques i condicions d'operació. Posteriorment, s'estudia l'impacte del mateix compressor sobre el procés de barreja i la condensació, cosa que permet després desacoblar el problema i reduir en dos ordres de magnitud el temps de càlcul, ja que pot obviar-se la simulació del compressor. Quant a la influència de la geometria en el marge de bombeig i la resta de paràmetres, es proposen diverses geometries senzilles i s'analitza el seu impacte. Primerament, es realitzen assajos experimentals en banc motor, tant estacionaris per mesurar rendiment i soroll com transitoris per definir el bombeig. Després, s'executen simulacions CFD i s'estudien els fenòmens locals que apareixen, en els quals s'evidencia una sensibilitat elevada de la geometria sobre el marge de bombeig i la resta de paràmetres. Es pot destacar el rendiment de la geometria d'entrada cònica, que produeix un augment considerable del marge de bombeig sense repercussions en la resta de condicions d'operació; i la tovera convergent-divergent, que augmenta el marge de bombeig però, a més, també augmenta lleugerament el rendiment en la resta del mapa del compressor, encara que a costa de reduir moderadament les prestacions a alt flux màssic. / Tarí De Paco, D. (2018). Effect of inlet configuration on the performance and durability of an automotive turbocharger compressor [Tesis doctoral no publicada]. Universitat Politècnica de València. https://doi.org/10.4995/Thesis/10251/104410 / TESIS

This thesis deals with CFD simulation of platooning vehicles and their aerodynamic characteristics, created in Star CCM+ software. The main focus is on their aerodynamic drag dependency on different spacing between vehicles which allowed to evaluate the most energy efficient distance for platoon of vehicles. Furthermore, the procedure how to calculate the fuel consumption is described for set of variables.

This diploma thesis is focused on the implementation of the technology VoIP in the remote branch offices of a big company. There are used the current WAN lines, which have been so far used only for transfer of data. Implementation of IP telephony is extending the utilization of those lines and at the same time the costs for running of the telephone services are reduced. There are described the models for proposal and also the proposal for solution of IP telephony for a specific company.

No description available.

Configurable computing machines (CCMs) offer high-performance application acceleration with custom hardware. They are also dynamically reconfigurable and give significant internal visibility. Such features are useful throughout the design, debug, and deploy stages of CCM-based application development. However traditional, monolithic design tools do not offer adequate support for all of these development stages. This thesis describes a specification for a reconfigurable computing application framework (RCAF) which is more suitable for CCM application development. It also describes an implementation of such an RCAF. This RCAF improves the efficiency of application design and debugging. It also establishes an application architecture framework which helps to build up not only the hardware design, but also the application software and user interface. Applications built using this small, deployable RCAF may also perform significantly better due to the dynamic hardware reconfiguration features included with the RCAF.

This project deals with the CFD modelling of a free surface flow. The aim is to develop and validate a fast and accurate numerical model for stratified two-phase flows. Volume of Fluid (VOF) multiphase model is employed. The purpose is to use the developed numerical model for the design of an element within a compact nuclear reactor.Unsteady Reynolds Averaged Navier-Stokes (RANS) simulations are conducted. Two free surface test cases are simulated to verify and ensure robustness of the model: a dam break and a vertical cylindrical obstacle set in a channel. From there, an optimization is performed in order to find the best compromise between accuracy and rapidity with the solver. The proper set of parameter models is found by carrying out extensive sensitivity studies and compare the solutions with available measurements.The obtained numerical results show a reasonable good agreement with the experimental data for the dam-break. Significant time savings are achieved thanks to the implemented optimization process while maintaining accuracy. The optimized model is then applied to the second test case and comparisons with experimental measurements are carried out. The same physical behavior of the flow as in experiments is captured with the simulations. The differences found between the simulation data and experiments are partly due to the difficulty to monitor experimentally with a high accuracy the highly non uniform regions within the flow.