Numerical simulation of group combustion of pulverized coal

A mathematical model for the group combustion of pulverized coal particles was developed in a previous work. It includes the Lagrangian description of the dehumidification, devolatilization and char gasification reactions of the coal particles in the homogenized gaseous environment resulting from the three fuels, CO, H2 and volatiles, supplied by the gasification of the particles and their simultaneous group combustion by the gas phase oxidation reactions, which are considered to be very fast. This model is complemented here with an analysis of the particle dynamics, determined principally by the effects of aerodynamic drag and gravity, and its dispersion based on a stochastic model. It is also extended to include two other simpler models for the gasification of the particles: the first one for particles small enough to extinguish the surrounding diffusion flames, and a second one for particles with small ash content when the porous shell of ashes remaining after gasification of the char, non structurally stable, is disrupted. As an example of the applicability of the models, they are used in the numerical simulation of an experiment of a non-swirling pulverized coal jet with a nearly stagnant air at ambient temperature, with an initial region of interaction with a small annular methane flame. Computational algorithms for solving the different stages undergone by a coal particle during its combustion are proposed. For the partial differential equations modeling the gas phase, a second order finite element method combined with a semi-Lagrangian characteristics method are used. The results obtained with the three versions of the model are compared among them and show how the first of the simpler models fits better the experimental results.

Uso del cálculo numérico CFD para el estudio de actuaciones de una motocicleta de competición = CFD analysis of a competition motorbike aerodynamic performance

Esta memoria pretende ilustrar el desarrollo del Proyecto de Fin de Carrera Uso del cálculo numérico CFD para el estudio de actuaciones de una motocicleta de competición de los alumnos Álvaro Ramos Cenzano y Mauro Botella Mompó. Se centra en el estudio de las fuerzas aerodinámicas ejercidas sobre una motocicleta de competición, en concreto de una Moto2 del campeonato de España de velocidad (CEV), por medio de programas de simulación. Los capítulos del 1 al 4, describen por qué surgió el Proyecto, los datos a tener en cuenta del reglamento oficial de Moto2 del CEV (centrándonos sobre todo en los aspectos que afectan a la Aerodinámica, como puede ser el carenado), y los objetivos que se pretenden hallar con este proyecto. Se hará una pequeña introducción a la aerodinámica general para después profundizar en la aerodinámica automovilística y sobretodo en la de las motocicletas. Pasando por el interés que tiene la aerodinámica a diferentes niveles (comercial y de competición), y su evolución a lo largo de la historia. Se analizarán los diferentes métodos de trabajo que se podrían usar para el estudio aerodinámico, centrándose sobre todo en la técnica de estudio informático por Dinámica de Fluidos Computacional o CFD. Dado que el proyecto está basado en unas motocicletas reales, surgirán una serie de problemas en el uso de los métodos numéricos que se irán solventando, intentando mantener la estructura lo más fiel posible a los modelos reales. Todos estos problemas y sus soluciones se detallarán con la intención de que puedan servir de ayuda para futuros estudios. Tras las simulaciones con los programas CFD correspondientes a los distintos modelos de motocicleta, se compararán los resultados para ayudar en la definición del modelo final. El proyecto concluirá con las conclusiones obtenidas por los alumnos.

A dynamic programming approach to the formulation and solution of finite element equations

A method for formulating and algorithmically solving the equations of finite element problems is presented. The method starts with a parametric partition of the domain in juxtaposed strips that permits sweeping the whole region by a sequential addition (or removal) of adjacent strips. The solution of the difference equations constructed over that grid proceeds along with the addition removal of strips in a manner resembling the transfer matrix approach, except that different rules of composition that lead to numerically stable algorithms are used for the stiffness matrices of the strips. Dynamic programming and invariant imbedding ideas underlie the construction of such rules of composition. Among other features of interest, the present methodology provides to some extent the analyst's control over the type and quantity of data to be computed. In particular, the one-sweep method presented in Section 9, with no apparent counterpart in standard methods, appears to be very efficient insofar as time and storage is concerned. The paper ends with the presentation of a numerical example

Development of Shape-Optimization Tools for the Aerodynamic Design of Turbomachinery Blades

The aim of this work is to develop an automated tool for the optimization of turbomachinery blades founded on an evolutionary strategy. This optimization scheme will serve to deal with supersonic blades cascades for application to Organic Rankine Cycle (ORC) turbines. The blade geometry is defined using parameterization techniques based on B-Splines curves, that allow to have a local control of the shape. The location in space of the control points of the B-Spline curve define the design variables of the optimization problem. In the present work, the performance of the blade shape is assessed by means of fully-turbulent flow simulations performed with a CFD package, in which a look-up table method is applied to ensure an accurate thermodynamic treatment. The solver is set along with the optimization tool to determine the optimal shape of the blade. As only blade-to-blade effects are of interest in this study, quasi-3D calculations are performed, and a single-objective evolutionary strategy is applied to the optimization. As a result, a non-intrusive tool, with no need for gradients definition, is developed. The computational cost is reduced by the use of surrogate models. A Gaussian interpolation scheme (Kriging model) is applied for the estimated n-dimensional function, and a surrogate-based local optimization strategy is proved to yield an accurate way for optimization. In particular, the present optimization scheme has been applied to the re-design of a supersonic stator cascade of an axial-flow turbine. In this design exercise very strong shock waves are generated in the rear blade suction side and shock-boundary layer interaction mechanisms occur. A significant efficiency improvement as a consequence of a more uniform flow at the blade outlet section of the stator is achieved. This is also expected to provide beneficial effects on the design of a subsequent downstream rotor. The method provides an improvement to gradient-based methods and an optimized blade geometry is easily achieved using the genetic algorithm.

Development of AMREM: a Maxwell's equations solver with Adaptive Mesh Refinement

El principal objetivo de la presente tesis es el de desarrollar y probar un código capaz de resolver las ecuaciones de Maxwell en el dominio del tiempo con Malla Refinada Adaptativa (AMR por sus siglas en inglés). AMR es una técnica de cálculo basada en dividir el dominio físico del problema en distintas mallas rectangulares paralelas a las direcciones cartesianas. Cada una de las mallas tendrá distinta resolución y aquellas con mayor resolución se sitúan allí dónde las ondas electromagnéticas se propagan o interaccionan con los materiales, es decir, dónde mayor precisión es requerida. Como las ondas van desplazándose por todo el dominio, las mayas deberán seguirlas. El principal problema al utilizar esta metodología se puede encontrar en las fronteras internas, dónde las distintas mallas se unen. Ya que el método más corrientemente utilizado para resolver las ecuaciones de Maxwell es el de las diferencias finitas en el dominio del tiempo (FDTD por sus siglas en inglés) , el trabajo comenzó tratando de adaptar AMR a FDTD. Tras descubrirse que esta interacción resultaba en problemas de inestabilidades en las fronteras internas antes citadas, se decidió cambiar a un método basado en volúmenes finitos en el dominio del tiempo (FVTD por sus siglas en inglés). Este se basa en considerar la forma en ecuaciones de conservación de las ecuaciones de Maxwell y aplicar a su resolución un esquema de Godunov. Se ha probado que es clave para el correcto funcionamiento del código la elección de un limitador de flujo que proteja los extremos de la onda de la disipación típica de los métodos de este tipo. Otro problema clásico a la hora de resolver las ecuaciones de Maxwell es el de tratar con las condiciones de frontera física cuando se simulan dominios no acotados, es decir, dónde las ondas deben salir del sistema sin producir ninguna reflexión. Normalmente la solución es la de disponer una banda absorbente en las fronteras físicas. En AMREM se ha desarrollado un nuevo método basado en los campos característicos que con menor requisito de CPU funcina suficientemente bien incluso en los casos más desfaborables. El código ha sido contrastado con soluciones analíticas de diferentes problemas y también su velocidad ha sido comparada con la de Meep, uno de los programas más conocidos del ámbito. También algunas aplicaciones han sido simuladas con el fin de demostrar el amplio espectro de campos en los que AMREM puede funcionar como una útil herramienta.

Aerodynamic loads on bluff bodies under wind gusts

Esta tesis doctoral se ha centrado en el estudio de las cargas aerodinámicas no estacionario en romos cuerpos o no aerodinámicos (bluff bodies). Con este objetivo se han identificado y analizado los siguientes puntos: -Caracterización del flujo medido con diferentes tipos de tubos de Pitot y anemómetro de hilo caliente en condiciones de flujo no estacionario inestable generado por un túnel aerodinamico de ráfagas. -Diseño e integración de los montajes experimentales requeridos para medir las cargas de viento internas y externas que actúan sobre los cuerpos romos en condiciones de flujo de viento con ráfagas. -Implementación de modelos matemáticos semi-empíricos basados en flujo potencial y las teorías fenomenológicas pertinentes para simular los resultados experimentales. -En diversan condiciones de flujo con ráfagas, la identificación y el análisis de la influencia de los parámetros obtenida a partir de los modelos teóricos desarrollados. -Se proponen estimaciones empíricas para averiguar los valores adecuados de los parámetros que influyente, mediante el ajuste de los resultados experimentales y los predichos teóricamente. Los montajes experimentales se has reakizado en un tunel aerodinamico de circuito abierto, provisto de baja velocidad, cámara de ensayes cerrada, un nuevo concepto de mecanismo generador de ráfaga sinusoidal, diseñado y construido en el Instituto de Microgravedad "Ignacio Da Riva" de la Universidad Politécnica de Madrid, (IDR / UPM). La principal característica de este túnel aerodynamico es la capacidad de generar un flujo con un perfil de velocidad uniforme y una fluctuación sinusoidal en el tiempo. Se han realizado pruebas experimentales para estudiar el efecto de los flujos no estacionarios en cuerpos romos situados en el suelo. Se han propuesto dos modelos teóricos para diterminar las cargas de presión externas e internas respectivamente. Con el fin de satisfacer la necesidad de la crea ráfagas de viento sinusoidales para comprobar las predicciones de los modelos teóricos, se han obtenido velocidades de hasta 30 m/s y frecuencias ráfaga de hasta 10 Hz. La sección de la cámara de ensayos es de 0,39 m x 0,54 m, dimensiónes adecuadas para llevar a cabo experimentos con modelos de ensayos. Se muestra que en la gama de parámetros explorados los resultados experimentales están en buen acuerdo con las predicciones de los modelos teóricos. Se han realizado pruebas experimentales para estudiar los efectos del flujo no estacionario, las cuales pueden ayudar a aclarar el fenómeno de las cargas de presión externa sobre los cuerpos romos sometidos a ráfagas de viento: y tambien para determinan las cargas de presión interna, que dependen del tamaño de los orificios de ventilación de la construcción. Por último, se ha analizado la contribución de los términos provenientes del flujo no estacionario, y se han caracterizado o los saltos de presión debido a la pérdida no estacionario de presión a través de los orificios de ventilación. ABSTRACT This Doctoral dissertation has been focused to study the unsteady aerodynamic loads on bluff bodies. To this aim the following points have been identified and analyzed: -Characterization of the flow measured with different types of Pitot tubes and hot wire anemometer at unsteady flow conditions generated by a gust wind tunnel. -Design and integrating of the experimental setups required to measure the internal and external wind loads acting on bluff bodies at gusty wind flow conditions. -Implementation of semi-empirical mathematical models based on potential flow and relevant phenomenological theories to simulate the experimental results.-At various gusty flow conditions, extracting and analyzing the influence of parameters obtained from the developed theoretical models. -Empirical estimations are proposed to find out suitable values of the influencing parameters, by fitting the experimental and theoretically predicted results. The experimental setups are performed in an open circuit, closed test section, low speed wind tunnel, with a new sinusoidal gust generator mechanism concept, designed and built at the Instituto de Microgravedad “Ignacio Da Riva” of the Universidad Politécnica de Madrid, (IDR/UPM). The main characteristic of this wind tunnel is the ability to generate a flow with a uniform velocity profile and a sinusoidal time fluctuation of the speed. Experimental tests have been devoted to study the effect of unsteady flows on bluff bodies lying on the ground. Two theoretical models have been proposed to measure the external and internal pressure loads respectively. In order to meet the need of creating sinusoidal wind gusts to check the theoretical model predictions, the gust wind tunnel maximum flow speed and, gust frequency in the test section have been limited to 30 m/s and 10 Hz, respectively have been obtained. The test section is 0.39 m × 0.54 m, which is suitable to perform experiments with testing models. It is shown that, in the range of parameters explored, the experimental results are in good agreement with the theoretical model predictions. Experimental tests have been performed to study the unsteady flow effects, which can help in clarifying the phenomenon of the external pressure loads on bluff bodies under gusty winds: and also to study internal pressure loads, which depend on the size of the venting holes of the building. Finally, the contribution of the unsteady flow terms in the theoretical model has been analyzed, and the pressure jumps due to the unsteady pressure losses through the venting holes have been characterized.

Genetically aerodynamic optimization of the nose shape of a high-speed train entering a tunnel

The optimization of the nose shape of a high-speed train entering a tunnel has been performed using genetic algorithms(GA).This optimization method requires the parameterization of each optimal candidate as a design vector.The geometrical parameterization of the nose has been defined using three design variables that include the most characteristic geometrical factors affecting the compression wave generated at the entry of the train and the aerodynamic drag of the train.

Aerodynamic shape optimization of the nose of a high-speed train subjected to crosswind conditions

When dealing with the design of a high-speed train, a multiobjective shape optimization problem is formulated, as these vehicles are object of many aerodynamic problems which are known to be in conflict. More mobility involves an increase in both the cruise speed and lightness, and these requirements directly influence the stability and the ride comfort of the passengers when the train is subjected to a side wind. Thus, crosswind stability plays a more relevant role among the aerodynamic objectives to be optimized. An extensive research activity is observed on aerodynamic response in crosswind conditions.

Aerodynamic Optimization of a High-speed Train using Genetic Algorithms

Genetic algorithms (GA) have been used for the minimization of the aerodynamic drag of a train subject to front wind. The significant importance of the external aerodynamic drag on the total resistance a train experiments as the cruise speed is increased highlights the interest of this study. A complete description of the methodology required for this optimization method is introduced here, where the parameterization of the geometry to be optimized and the metamodel used to speed up the optimization process are detailed. A reduction of about a 25% of the initial aerodynamic drag is obtained in this study, what confirms GA as a proper method for this optimization problem. The evolution of the nose shape is consistent with the literature. The advantage of using metamodels is stressed thanks to the information of the whole design space extracted from it. The influence of each design variable on the objective function is analyzed by means of an ANOVA test.

Flight loads analysis of a maneuvering transport aircraft

The paper provides a method applicable for the determination of flight loads for maneuvering aircraft, in which aerodynamic loads are calculated based on doublet lattice method, which contains three primary steps. Firstly, non-dimensional stability and control derivative coefficients are obtained through solving unsteady aerodynamics in subsonic flow based on a doublet lattice technical. These stability and control derivative coefficients are used in second step. Secondly, the simulation of aircraft dynamic maneuvers is completed utilizing fourth order Runge-Kutta method to solve motion equations in different maneuvers to gain response parameters of aircraft due to the motion of control surfaces. Finally, the response results calculated in the second step are introduced to the calculation of aerodynamic loads. Thus, total loads and loads distribution on different components of aircraft are obtained. According to the above method, abrupt pitching maneuvers, rolling maneuvers and yawing maneuvers are investigated respectively.

On the effects of windbreaks on the aerodynamic loads over parabolic solar troughs

Parabolic reflectors, also known as parabolic troughs, are widely used in solar thermal power plants. This kind of power plants is usually located on desert climates, where the combined action of wind and dust can be of paramount importance. In some cases it becomes necessary to protect these devices from the joined wind and sand action, which is normally accomplished through solid windbreaks. In this paper the results of a wind tunnel test campaign, of a scale parabolic trough row having different windward windbreaks, are reported. The windbreaks herein considered consist of a solid wall with an upper porous fence. Different geometrical configurations, varying the solid wall height and the separation between the parabolic trough row and the windbreak have been considered. From the measured time series, both the mean and peak values of the aerodynamic loads were determined. As it would be expected, mean aerodynamic drag, as well as peak values, decrease as the distance between the windbreak and the parabolic increases, and after a threshold value, such drag loads increase with the distance.