Validación del método de predicción de direcciones principales de drenaje subterráneo en macizos anisótropos, en los terrenos volcánicos del macizo de Anaga, Tenerife

Actualmente y desde hace ya más de 25 años, el Método de “Predicción de las Direcciones Principales de Drenaje Subterráneo en Macizos Anisótropos”, ha sido utilizado con éxito en diferentes terrenos Kársticos como: calizas, yesos, cuarcitas, pizarras, granitos y criokarst (karst en el hielo glaciar). Sin embargo hasta ahora, nunca se había validado en terrenos volcánicos donde está focalizada esta tesis que lleva por título, Validación de dicho Método en los Terrenos Volcánicos del Macizo de Anaga en Tenerife. Este Método matemático consiste esencialmente en “Predecir y Cuantificar” las direcciones principales de drenaje turbulento subterráneo en macizos anisótropos. Para ello se basa en el estudio realizado en campo de los tectoglifos o deformaciones permanentes del macizo, impresas éstas en la roca, como consecuencia de los esfuerzos tectónicos a los que ha estado sometido dicho macizo. Se consigue de esta manera cubrir el vacío para macizos anisótropos que existe con el modelo matemático de flujo subterráneo laminar (macizos isótropos) definido por Darcy (1856). Para validar el Método se ha elegido el macizo de Anaga, pues es la zona de mayor anisotropía existente en la isla de Tenerife, conformada por una gran y extensa red de diques de diversas formas y tamaños que pertenecen a la familia de diques del eje estructural NE de la isla. En dicho macizo se realizó un exhaustivo trabajo de campo con la toma 331 datos (diques basálticos) y se aplicó el Método, consiguiendo definir las direcciones preferentes de drenaje subterráneo en el macizo de Anaga. Esta predicción obtenida se contrastó con la realidad del drenaje en la zona, conocida gracias a la existencia de cinco galerías ubicadas en la zona trabajo, de las cuales se tiene información sobre sus alumbramientos. En todos los casos se demuestra la bondad de la predicción obtenida con el Método. Queda demostrado que a mayor caos geológico o geotectónico, se ha conseguido mejor predicción del Método, obteniéndose resultados muy satisfactorios para aquellas galerías de agua en las que su rumbo de avance fue coincidente con la dirección perpendicular a la obtenida con la predicción dada por el Método, como dirección preferente de drenaje en la zona en la que se encuentra ubicada cada galería. No cabe duda que la validación de Método en los terrenos volcánicos de Tenerife, supondrá un cambio considerable en el mundo de la hidrogeología en este tipo de terrenos. Es la única herramienta matemática que se dispone para predecir un rumbo acertado en el avance de la perforación de las galerías de aguas, lo que conlleva al mismo tiempo un ahorro importantísimo en la ejecución de las obras. Por otro lado, el Método deja un importante legado a la sociedad canaria, pues con él se abren numerosas vías de trabajo e investigación que generarán un importante desarrollo en el mundo de la hidrogeología volcánica. ABSTRACT Currently and for over 25 years now, the Method of "Prediction of Subsurface Drainage Main Directions in Anisotropic Massifs" has been successfully used in various karstic terrains such as: limestone, gypsum, quartzite, slate, granite and criokarst (karst in the glacier ice). However, until now, it had never been validated in volcanic terrains where is focused this thesis entitled Validation of such Method in the Anaga Massif Volcanic Terrains, in Tenerife. This mathematical method is essentially "predict and quantify" the main directions of groundwater turbulent drainage in anisotropic massifs. This is based on field study of tectoglifes or permanent deformation of the massif, printed on the rocks as a result of previous tectonic stresses. Therefore it is possible to use in anisotropic rock mathematical model instead of the isotropic laminar flow mathematical models defined by Darcy (1856). The Anaga Massif have been chosen to validate the method, because it presents the greatest anisotropy in Tenerife Island, shaped by a large and extensive network of dikes of various shapes and sizes that belong to the family of NE structural axis dikes of the island. An exhaustive field work was carried out in such massif, with 331 collected data (basaltic dikes) and the method was applied, in order to define the preferred direction of the underground drainage in the Anaga massif. This obtained prediction was contrasted to the reality of the drainage in the area, known thanks to the existence of five galleries located in the work area, from which information about their springs was available. In all cases it was possible to demonstrate the fitness of the prediction obtained by the method. It had been demonstrated that a greater geological or geotectonic chaos enhances a better prediction of the method, that predicted very satisfactory results for those water galleries which directions were perpendicular to that predicted by the Method as a drainage preferential direction, for the zone where was located each gallery. No doubt that the validation of the use of the Method in the volcanic terrain of Tenerife, means a considerable change in the world of hydrogeology in this type of terrain. It is the only mathematical tool available to predict a successful drilling direction in advancing water galleries, what also leads to major savings in execution of the drilling works. Furthermore, the method leaves an important legacy to the Canary Islands society, because it opens many lines of work and research to generate a significant development in the world of volcanic hydrogeology.

La hidráulica kárstica como aplicación de la hidrodinámica general. Estudio del flujo en un terreno yesífero fisurado

Se pretende plantear y desarrollar algunas de las leyes clásicas de hidrodinámica introduciendo las características que permiten su aplicación al flujo subterráneo en general y a la hidráulica kárstica en particular. Se estudia la consideración de si el movimiento del agua subterránea en el karst se puede definir como flujo a través de conductos individuales o como un medio continuo con huecos saturados en una matriz sólida. Los trabajos de Hagen (1839) y Poiseuille (1846), junto con los de Darcy (1856) configuran la referencia básica para este estudio (in Crespo, 2006). A ellos puede añadirse también las aportaciones de Couette y Chezy (Rouse, 1951) para flujo libre sobre superficies rocosas. Se presentan varios casos en los que las leyes del movimiento laminar unidireccional ofrecen soluciones que pueden ser válidas para la definición de los parámetros fundamentales del flujo del agua en el subsuelo.

Horizontal visibility graphs generated by type-I intermittency

The type-I intermittency route to (or out of) chaos is investigated within the horizontal visibility (HV) graph theory. For that purpose, we address the trajectories generated by unimodal maps close to an inverse tangent bifurcation and construct their associatedHVgraphs.We showhowthe alternation of laminar episodes and chaotic bursts imprints a fingerprint in the resulting graph structure. Accordingly, we derive a phenomenological theory that predicts quantitative values for several network parameters. In particular, we predict that the characteristic power-law scaling of the mean length of laminar trend sizes is fully inherited by the variance of the graph degree distribution, in good agreement with the numerics. We also report numerical evidence on how the characteristic power-law scaling of the Lyapunov exponent as a function of the distance to the tangent bifurcation is inherited in the graph by an analogous scaling of block entropy functionals defined on the graph. Furthermore, we are able to recast the full set of HV graphs generated by intermittent dynamics into a renormalization-group framework, where the fixed points of its graph-theoretical renormalization-group flow account for the different types of dynamics.We also establish that the nontrivial fixed point of this flow coincides with the tangency condition and that the corresponding invariant graph exhibits extremal entropic properties.

Theory of intermittency applied to classical pathological cases

The classical theory of intermittency developed for return maps assumes uniform density of points reinjected from the chaotic to laminar region. Though it works fine in some model systems, there exist a number of so-called pathological cases characterized by a significant deviation of main characteristics from the values predicted on the basis of the uniform distribution. Recently, we reported on how the reinjection probability density (RPD) can be generalized. Here, we extend this methodology and apply it to different dynamical systems exhibiting anomalous type-II and type-III intermittencies. Estimation of the universal RPD is based on fitting a linear function to experimental data and requires no a priori knowledge on the dynamical model behind. We provide special fitting procedure that enables robust estimation of the RPD from relatively short data sets (dozens of points). Thus, the method is applicable for a wide variety of data sets including numerical simulations and real-life experiments. Estimated RPD enables analytic evaluation of the length of the laminar phase of intermittent behaviors. We show that the method copes well with dynamical systems exhibiting significantly different statistics reported in the literature. We also derive and classify characteristic relations between the mean laminar length and main controlling parameter in perfect agreement with data provided by numerical simulations

Accurate Parabolic Navier-Stokes solutions of the supersonic flow around and elliptic cone

Flows of relevance to new generation aerospace vehicles exist, which are weakly dependent on the streamwise direction and strongly dependent on the other two spatial directions, such as the flow around the (flattened) nose of the vehicle and the associated elliptic cone model. Exploiting these characteristics, a parabolic integration of the Navier-Stokes equations is more appropriate than solution of the full equations, resulting in the so-called Parabolic Navier-Stokes (PNS). This approach not only is the best candidate, in terms of computational efficiency and accuracy, for the computation of steady base flows with the appointed properties, but also permits performing instability analysis and laminar-turbulent transition studies a-posteriori to the base flow computation. This is to be contrasted with the alternative approach of using order-of-magnitude more expensive spatial Direct Numerical Simulations (DNS) for the description of the transition process. The PNS equations used here have been formulated for an arbitrary coordinate transformation and the spatial discretization is performed using a novel stable high-order finite-difference-based numerical scheme, ensuring the recovery of highly accurate solutions using modest computing resources. For verification purposes, the boundary layer solution around a circular cone at zero angle of attack is compared in the incompressible limit with theoretical profiles. Also, the recovered shock wave angle at supersonic conditions is compared with theoretical predictions in the same circular-base cone geometry. Finally, the entire flow field, including shock position and compressible boundary layer around a 2:1 elliptic cone is recovered at Mach numbers 3 and 4

Análisis de la influencia del borde de salida abierto en perfiles aerodinámicos a bajos números de Reynolds

El objetivo del presente trabajo es analizar la influencia que tiene sobre el comportamiento aerodinámico del perfil el hecho de que este presente un borde de salida más grueso que el perfil original del que se partía. Este estudio se ha centrado fundamentalmente en la influencia sobre su sustentación aerodinámica, resistencia aerodinámica y, especialmente, sobre la eficiencia aerodinámica del perfil, es decir sobre la relación entre la sustentación y la resistencia aerodinámica. También se ha analizado su influencia en otros aspectos aerodinámicos de los perfiles, como la entrada en pérdida, el ángulo de ataque de sustentación máxima, el ángulo de ataque de eficiencia máxima, el coeficiente de momento aerodinámico y la posición del centro aerodinámico. Estas imperfecciones en el borde de salida pueden aparecer en algunos procesos de fabricación de determinados elementos aerodinámicos, como alas de aviones no tripulados o palas de aeroturbina. Este fenómeno no ha sido analizado en profundidad en la literatura científica, aunque si que se ha analizado por varios autores la influencia sobre el perfil con el borde de salida truncado, o perfiles con la parte final regruesada, utilizados en otras aplicaciones. Para la realización de este estudio se han analizado perfiles de distinto tipo, laminares y no laminares, perfiles simétricos y con curvatura, así como perfiles con distinto espesor, a fin de comparar el grado de influencia del fenómeno estudiado sobre cada tipo de perfil para comparar su grado de sensibilidad a dicha anomalía geométrica. El estudio se ha realizado experimentalmente utilizando una cámara de ensayos diseñada específicamente a tal efecto, así como una balanza electrónica para medir las fuerzas y los momentos sobre el perfil, y un escáner de presiones para medir la distribución de presiones en determinados casos. También se ha abordado el estudio del comportamiento de perfiles con borde de salida más grueso que el nominal pero redondeado en vez de romo, con el objeto de analizar la eficacia de redondear el borde de salida, que es uno de los métodos que se puede utilizar para mitigar este efecto. Por otro lado, como el comportamiento de los perfiles aerodinámicos tiene una fuerte dependencia del número de Reynolds, el estudio se ha centrado en el análisis del comportamiento a bajos números de Reynolds debido a su uso reciente en una amplia gama de aplicaciones, desde vehículos aéreos no tripulados (UAV) hasta palas de aeroturbinas de baja potencia, e incluso debido a su uso potencial en aeronaves diseñadas para volar en atmósferas de baja densidad como la que existe en Marte. El interés de este estudio está orientado al establecimiento de criterios para cuantificar la influencia que tiene el hecho de que el borde de salida sea más grueso que el nominal en la degradación de su eficiencia aerodinámica máxima, con el objeto de poder establecer los límites de aceptación o rechazo de estas piezas una vez fabricadas, según el tipo de perfil aerodinámico utilizado. Del resultado del análisis de los casos estudiados se puede concluir que según aumenta el espesor del borde de salida, dentro del intervalo de estudio, la sustentación aerodinámica aumenta, así como la sustentación máxima, pero aumenta en mayor proporción la resistencia aerodinámica, por lo que se produce una reducción de la eficiencia aerodinámica, en particular de su valor máximo. Por otro lado, el hecho de redondear el borde de salida del perfil ayuda ligeramente a reducir este efecto. ABSTRACT The aim of this thesis is to analyze the effects of airfoil trailing edges thickness when this is thicker than the airfoil nominal. Several factors may lead to an airfoil trailing edge being thicker than the nominal airfoil, and this may affect various aerodynamic parameters. This study has focus on its influence on the airfoil’s aerodynamic lift, drag and, particularly on the aerodynamic efficiency of the airfoil, that is, the relationship between the aerodynamic lift and drag. It has also been studied how this fact may alter some other aerodynamic aspects of airfoils, such as stall, angle of attack of maximum lift, angle of maximum efficiency, aerodynamic moment coefficient and aerodynamic center position. These imperfections in the trailing edge may appear in some manufacturing processes of certain aerodynamic elements, such as unmanned aircraft wings or wind turbine blades. This phenomenon has not been deeply analyzed in the literature, although several authors have discussed its influence on airfoil with truncated trailing edge, or airfoils with thickened end, used in other applications. Various types of airfoils have been analyzed, laminar and non-laminar, symmetric and curved airfoils, and airfoils with different thickness, in order to compare the degree of influence of the phenomenon studied on each airfoil type and thus, to estimate the degree of sensitivity to the anomaly geometry. The study was carried out experimentally using a test chamber designed specifically for this purpose, as well as an electronic balance to measure the forces and moments on the airfoil, and a pressure scanner to measure distribution of pressures in certain cases. It has also been investigated the behavior of airfoils with trailing edge thicker than the nominal, but rounded instead of blunt, in order to analyze the effectiveness of the trailing edge rounding, which is one of the methods that can be used to mitigate this phenomenon. Moreover, as the behavior of the airfoil is highly dependent on the Reynolds number, the study has been focused on the analysis of the behavior at low Reynolds numbers due to recent use of low Reynolds numbers airfoils in a wide range of applications, from unmanned aerial vehicles (UAV) to low power wind turbine blades, or even due to their potential use in aircraft designed to fly in low density atmospheres as the one existing in Mars. The main purpose of this research is to establish a set of criteria for quantifying the influence that a thicker-than–nominal-trailing edge has in the degradation of maximum aerodynamic efficiency, aiming at establishing the acceptance limits for these pieces when they are manufactured, according to the type of airfoil used. Based on the results obtained from the analysis of the cases under study it can be concluded that increasing the thickness of the trailing edge, within the range of study, increases aerodynamic lift, as well as maximum lift, but the aerodynamic drag increases in a higher proportion, and consequently there is a reduction of aerodynamic efficiency, particularly, of its maximum value. On the other hand, rounding the trailing edge of the airfoil slightly helps to reduce this effect.

Análisis de la influencia de imperfecciones en el borde de ataque en perfiles aerodinámicos a bajos números de Reynolds

En esta tesis se ha analizado la influencia que tienen ciertas imperfecciones en el borde de ataque de un perfil aerodinámico sobre el comportamiento aerodinámico general del mismo, centrándose fundamentalmente en la influencia sobre el coeficiente de sustentación máxima, coeficiente de resistencia y sobre la eficiencia aerodinámica del perfil, es decir sobre la relación entre la sustentación y la resistencia aerodinámicas. También se ha analizado su influencia en otros aspectos, como la entrada en pérdida, ángulo de ataque de sustentación máxima, ángulo de ataque de eficiencia máxima, coeficiente de momento aerodinámico y posición del centro aerodinámico. Estos defectos de forma en el borde de ataque pueden aparecer en algunos procesos de fabricación de determinados elementos aerodinámicos, como pueden ser las alas de pequeños aviones no tripulados o las palas de aeroturbina. Los perfiles se ha estudiado a bajos números de Reynolds debido a su uso reciente en una amplia gama de aplicaciones, desde vehículos aéreos no tripulados (UAV) hasta palas de aeroturbina de baja potencia, e incluso debido a su potencial utilización en aeronaves diseñadas para volar en atmósferas de baja densidad. El objeto de estudio de esta tesis no ha sido analizado en profundidad en la literatura científica, aunque sí que se ha estudiado por varios autores el comportamiento de perfiles a bajos números de Reynolds, con ciertas protuberancias sobre su superficie o también con formación de hielo en el borde de ataque. Para la realización de este estudio se han analizado perfiles de distinto tipo, perfiles simétricos y con curvatura, perfiles laminares, y todos ellos con igual o distinto espesor, con el objeto de obtener y comparar la influencia del fenómeno estudiado sobre cada tipo de perfil y así analizar su grado de sensibilidad a estas imperfecciones en la geometría del borde de ataque. Este trabajo ha sido realizado experimentalmente utilizando una túnel aerodinámico diseñado específicamente a tal efecto, así como una balanza electrónica para medir las fuerzas y los momentos sobre el perfil, y un escáner de presiones para medir la distribución de presiones sobre la superficie de los perfiles en determinados casos de interés. La finalidad de este estudio está orientada al establecimiento de criterios para cuantificar la influencia en la aerodinámica del perfil que tiene el hecho de que el borde de ataque presente una discontinuidad geométrica, con el objeto de poder establecer los límites de aceptación o rechazo de estas piezas en el momento de ser fabricadas. Del análisis de los casos estudiados se puede concluir que según aumenta el tamaño de la imperfección del borde de ataque, la sustentación aerodinámica máxima en general disminuye, al igual que la eficiencia aerodinámica máxima, pues la resistencia aerodinámica aumenta. Sin embargo, en algunos casos, para pequeños defectos se produce un efecto contrario. La sustentación máxima aumenta apreciablemente sin apenas pérdida de eficiencia aerodinámica máxima. ABSTRACT The aim of this thesis is to analyze the effects of leading edge imperfections on the aerodynamic characteristics of airfoils at low Reynolds numbers. The leading edge imperfection here considered being a slight displacement of half airfoil with respect to the other. This study has focus on its influence on the airfoil’s aerodynamic lift, drag and on the aerodynamic efficiency of the airfoil, that is, the relationship between the aerodynamic lift and drag. It has also been studied how this fact may alter some other aerodynamic aspects of airfoils, such as stall, angle of attack of maximum lift, angle of maximum efficiency, aerodynamic moment coefficient and aerodynamic center position. These imperfections in the leading edge may appear in some manufacturing processes of certain aerodynamic elements, such as unmanned aircraft wings or wind turbine blades. The study has focused on the analysis of the behavior at low Reynolds numbers due to recent use of low Reynolds numbers airfoils in a wide range of applications, from unmanned aerial vehicles (UAV) to low power wind turbine blades, or even due to their potential use in aircraft designed to fly in low density atmospheres as the one existing in Mars. This phenomenon has not been deeply analyzed in the literature, although several authors have discussed on airfoils at low Reynolds number, with leading edge protuberances or airfoils with ice accretions. Various types of airfoils have been analyzed, laminar and non-laminar, symmetric and curved airfoils, and airfoils with different thickness, in order to compare the degree of influence of the phenomenon studied on each airfoil type and thus, to estimate the degree of sensitivity to the anomaly geometry. The study was carried out experimentally using a test chamber designed specifically for this purpose, as well as an electronic balance to measure the forces and moments on the airfoil, and a pressure scanner to measure distribution of pressures in certain cases. The main purpose of this research is to establish a criteria for quantifying the influence that a slight displacement of half aerofoil with respect to the other has in the degradation of aerodynamics characteristics, aiming at establishing the acceptance limits for these pieces when they are manufactured, according to the type of airfoil used. Based on the results obtained from the analysis of the cases under study it can be concluded that displacements, within the range of study, decreases maximum aerodynamic lift, but the aerodynamic drag increases, and consequently there is a reduction of aerodynamic efficiency. However, in some cases, for small defects opposite effect occurs. The maximum lift increases significantly with little loss of maximum aerodynamic efficiency.

Influence of Strouhal number on pulsating methane–air coflow jet diffusion flames

Four periodically time-varying methane–air laminar coflow jet diffusion flames, each forced by pulsating the fuel jet's exit velocity Uj sinusoidally with a different modulation frequency wj and with a 50% amplitude variation, have been computed. Combustion of methane has been modeled by using a chemical mechanism with 15 species and 42 reactions, and the solution of the unsteady Navier–Stokes equations has been obtained numerically by using a modified vorticity-velocity formulation in the limit of low Mach number. The effect of wj on temperature and chemistry has been studied in detail. Three different regimes are found depending on the flame's Strouhal number S=awj/Uj, with a denoting the fuel jet radius. For small Strouhal number (S=0.1), the modulation introduces a perturbation that travels very far downstream, and certain variables oscillate at the frequency imposed by the fuel jet modulation. As the Strouhal number grows, the nondimensional frequency approaches the natural frequency of oscillation of the flickering flame (S≃0.2). A coupling with the pulsation frequency enhances the effect of the imposed modulation and a vigorous pinch-off is observed for S=0.25 and S=0.5. Larger values of S confine the oscillation to the jet's near-exit region, and the effects of the pulsation are reduced to small wiggles in the temperature and concentration values. Temperature and species mass fractions change appreciably near the jet centerline, where variations of over 2% for the temperature and 15% and 40% for the CO and OH mass fractions, respectively, are found. Transverse to the jet movement, however, the variations almost disappear at radial distances on the order of the fuel jet radius, indicating a fast damping of the oscillation in the spanwise direction.

Sheath vaporization of a monodisperse fuel-spray jet

The group vaporization of a monodisperse fuel-spray jet discharging into a hot coflowing gaseous stream is investigated for steady flow by numerical and asymptotic methods with a two-continua formulation used for the description of the gas and liquid phases. The jet is assumed to be slender and laminar, as occurs when the Reynolds number is moderately large, so that the boundary-layer form of the conservation equations can be employed in the analysis. Two dimensionless parameters are found to control the flow structure, namely the spray dilution parameter 1, defined as the mass of liquid fuel per unit mass of gas in the spray stream, and the group vaporization parameter e, defined as the ratio of the characteristic time of spray evolution due to droplet vaporization to the characteristic diffusion time across the jet. It is observed that, for the small values of e often encountered in applications, vaporization occurs only in a thin layer separating the spray from the outer droplet-free stream. This regime of sheath vaporization, which is controlled by heat conduction, is amenable to a simplified asymptotic description, independent of ε,in which the location of the vaporization layer is determined numerically as a free boundary in a parabolic problem involving matching of the separate solutions in the external streams, with appropriate jump conditions obtained from analysis of the quasi-steady vaporization front. Separate consideration of dilute and dense sprays, corresponding, respectively, to the asymptotic limits λ<<1 and λ>>1, enables simplified descriptions to be obtained for the different flow variables, including explicit analytic expressions for the spray penetration distance.

Dynamics of thermal ignition of spray flames in mixing layers

Conditions are identified under which analyses of laminar mixing layers can shed light on aspects of turbulent spray combustion. With this in mind, laminar spray-combustion models are formulated for both non-premixed and partially premixed systems. The laminar mixing layer separating a hot-air stream from a monodisperse spray carried by either an inert gas or air is investigated numerically and analytically in an effort to increase understanding of the ignition process leading to stabilization of high-speed spray combustion. The problem is formulated in an Eulerian framework, with the conservation equations written in the boundary-layer approximation and with a one-step Arrhenius model adopted for the chemistry description. The numerical integrations unveil two different types of ignition behaviour depending on the fuel availability in the reaction kernel, which in turn depends on the rates of droplet vaporization and fuel-vapour diffusion. When sufficient fuel is available near the hot boundary, as occurs when the thermochemical properties of heptane are employed for the fuel in the integrations, combustion is established through a precipitous temperature increase at a well-defined thermal-runaway location, a phenomenon that is amenable to a theoretical analysis based on activation-energy asymptotics, presented here, following earlier ideas developed in describing unsteady gaseous ignition in mixing layers. By way of contrast, when the amount of fuel vapour reaching the hot boundary is small, as is observed in the computations employing the thermochemical properties of methanol, the incipient chemical reaction gives rise to a slowly developing lean deflagration that consumes the available fuel as it propagates across the mixing layer towards the spray. The flame structure that develops downstream from the ignition point depends on the fuel considered and also on the spray carrier gas, with fuel sprays carried by air displaying either a lean deflagration bounding a region of distributed reaction or a distinct double-flame structure with a rich premixed flame on the spray side and a diffusion flame on the air side. Results are calculated for the distributions of mixture fraction and scalar dissipation rate across the mixing layer that reveal complexities that serve to identify differences between spray-flamelet and gaseous-flamelet problems.

Variable-density jet flows induced by concentrated sources of momentum and energy

The planar and axisymmetric variable-density flows induced in a quiescent gas by a concentrated source of momentum that is simultaneously either a source or a sink of energy are investigated for application to the description of the velocity and temperature far fields in laminar gaseous jets with either large or small values of the initial jet-to-ambient temperature ratio. The source fluxes of momentum and heat are used to construct the characteristic scales of velocity and length in the region where the density differences are of the order of the ambient density, which is slender for the large values of the Reynolds number considered herein. The problem reduces to the integration of the dimensionless boundary-layer conservation equations, giving a solution that depends on the gas transport properties but is otherwise free of parameters. The boundary conditions at the jet exit for integration are obtained by analysing the self-similar flow that appears near the heat source in planar and axisymmetric configurations and also near the heat sink in the planar case. Numerical integrations of the boundary-layer equations with these conditions give solutions that describe accurately the velocity and temperature fields of very hot planar and round jets and also of very cold plane jets in the far field region where the density and temperature differences are comparable to the ambient values. Simple scaling arguments indicate that the point source description does not apply, however, to cold round jets, whose far field region is not large compared with the jet development region, as verified by numerical integrations

Flamelet structures in spray ignition

In typical liquid-fueled burners the fuel is injected as a high-velocity liquid jet that breaks up to form the spray. The initial heating and vaporization of the liquid fuel rely on the relatively large temperatures of the sourrounding gas, which may include hot combustion products and preheated air. The heat exchange between the liquid and the gas phases is enhanced by droplet dispersion arising from the turbulent motion. Chemical reaction takes place once molecular mixing between the fuel vapor and the oxidizer has occurred in mixing layers separating the spray flow from the hot air stream. Since in most applications the injection velocities are much larger than the premixed-flame propagation velocity, combustion stabilization relies on autoignition of the fuel-oxygen mixture, with the combustion stand-off distance being controlled by the interaction of turbulent transport, droplet heating and vaporization, and gas-phase chemical reactions. In this study, conditions are identified under which analyses of laminar flamelets canshed light on aspects of turbulent spray ignition. This study extends earlier fundamental work by Liñan & Crespo (1976) on ignition in gaseous mixing layers to ignition of sprays. Studies of laminar mixing layers have been found to be instrumental in developing un-derstanding of turbulent combustion (Peters 2000), including the ignition of turbulent gaseous diffusion flames (Mastorakos 2009). For the spray problem at hand, the configuration selected, shown in Figure 1, involves a coflow mixing layer formed between a stream of hot air moving at velocity UA and a monodisperse spray moving at velocity USUA. The boundary-layer approximation will be used below to describe the resulting sl ender flow, which exhibits different igniting behaviors depending on the characteristics of t he fuel. In this approximation, consideration of the case U A = U S enables laminar ignition distances to be related to ignition times of unstrained spray flamelets, thereby pro viding quantitative information of direct applicability in regions of low scala r dissipation-rate in turbulent reactive flows (see the discussion in pp. 181–186 of Peters (2000)) . This report is organized as follows. Effects of droplet dispersion dynamics on ignition of sprays in turbulent mixing layers are discussed in Section 2. The formulation f or ignition in laminar mixing layers is outlined in Sections 3 and 4. The results are presented in Section 5. In Section 6, the mixture-fraction field and associated scalar dissipat ion rates for spray ignition are discussed. Finally, some brief conclusions are drawn in Section 7.

Type-I intermittency with discontinuous reinjection probability density in a truncation model of the derivative nonlinear Schrödinger equation

In previous papers, the type-I intermittent phenomenon with continuous reinjection probability density (RPD) has been extensively studied. However, in this paper type-I intermittency considering discontinuous RPD function in one-dimensional maps is analyzed. To carry out the present study the analytic approximation presented by del Río and Elaskar (Int. J. Bifurc. Chaos 20:1185-1191, 2010) and Elaskar et al. (Physica A. 390:2759-2768, 2011) is extended to consider discontinuous RPD functions. The results of this analysis show that the characteristic relation only depends on the position of the lower bound of reinjection (LBR), therefore for the LBR below the tangent point the relation {Mathematical expression}, where {Mathematical expression} is the control parameter, remains robust regardless the form of the RPD, although the average of the laminar phases {Mathematical expression} can change. Finally, the study of discontinuous RPD for type-I intermittency which occurs in a three-wave truncation model for the derivative nonlinear Schrodinger equation is presented. In all tests the theoretical results properly verify the numerical data

Adaptación de una central térmica de carbón a la Directiva de Emisiones Industriales

El proyecto que se presenta a continuación recoge la adaptación de una Central Térmica de carbón al cumplimiento de la DIRECTIVA 2010/75/UE DEL PARLAMENTO EUROPEO Y DEL CONSEJO de 24 de noviembre de 2010 sobre las emisiones industriales. La Central sobre la que se realiza el proyecto tiene un grupo térmico de carbón suscritico refrigerado por agua, con una potencia a plena carga de 350 MWe y de 190 MWe a mínimo técnico. Genera 1 090 t/h de vapor a 540 °C y 168 kg/cm2 funcionando a plena carga. Actualmente las emisiones de NOx son de 650 mg/m3, (condiciones normales, seco, 6 % O2). El objeto del proyecto es reducir estas emisiones a un valor máximo de 200 mg/m3 en las mismas condiciones. El proyecto analiza detalladamente las condiciones actuales de operación de la instalación en cuanto a combustible utilizado, horas de funcionamiento, condiciones climáticas y producción. Se analiza así mismo, todas las técnicas disponibles en mercado para la reducción del NOx, diferenciando entre medidas primarias (actúan sobre los efectos de formación) y secundarias (limpieza de gases). Las medidas primarias ya están implementadas en la central, por tanto, el proyecto plantea la reducción con medidas secundarias. De las medidas secundarias analizadas se ha seleccionado la instalación de un Reactor de Reducción Selectiva Catalítica (Reactor SCR). Tras un análisis de los diferentes reactores y catalizadores disponibles se ha seleccionado un reactor de configuración High-dust, una disposición de catalizador en 3 capas más 1, cuyos componentes están basados en óxidos metálicos (TiO2, V2O5, WO3) y estructura laminar. Se ha buscado la instalación del reactor para operar a una temperatura inferior a 450 °C. Como agente reductor se ha seleccionado NH3 a una dilución del 24,5 %. El proyecto recoge también el diseño de todo el sistema de almacenamiento, evaporación, dilución e inyección de amoniaco. El resultado del proyecto garantiza una concentración en los gases de salida por la chimenea inferior 180 mg/m3(n) de NOx. La reducción del NOx a los límites establecidos, tienen un coste por MWh neto generado para la central, trabajando 60 % a plena carga y 40 % a mínimo técnico y una amortización de 10 años, de 4,10 €/MWh. ABSTRACT The following project shows the compliance adjustment of a coal-fired power station to the 2010/75/EU Directive of the European Parliament and Council 24th November 2010 on industrial emissions. The project is based on a power station with a subcritical thermal coal unit, cooled with water, with a maximum power of 350 MWe and a technical minimum of 190 MWe. It produces 1 090 t/h of steam at 540 ° C and 168 kg/cm2 operating under full load. Currently, NOx emissions are 650 mg / m3 (normal conditions, dry, 6% O2). The project aims to reduce these emissions to a maximum value of 200 mg / m3 under the same conditions. The project analyses in detail the current operating conditions of the system in terms of fuel used, hours of operation, climatic conditions and production. In addition, it also analyses every available technique of NOx reduction on the market, distinguishing between primary (acting on the effects of formation) and secondary measures (gas cleaning). Primary measures are already implemented in the plant, thus proposing reduction with secondary measures. Among the secondary measures analyzed, it has been selected to install a Selective Catalytic Reduction Reactor (SCR Reactor). Having researched the different reactors and catalysts available, for the reactor has been selected High-dust configuration, an arrangement of catalyst in 3 layers plus 1, whose components are based on metal oxides (TiO2, V2O5, WO3) and laminar structure. The reactor has been sought facility to operate at a temperature below 450 ° C. NH3 diluted to 24,5 % has been selected as reducing agent. The project also includes the design of the entire storage system, evaporation, dilution and ammonia injection. The results of the project ensure a gas concentration in the lower chimney exit below 180 mg / m3(n) NOx. The reduction of NOx to the established limits has a cost per net MWh generated in the plant, working at 60% of full load and at 40% of technical minimum, with an amortization of 10 years, 4,10 € / MWh.

On the Use of Matrix-Free Shift-Invert Strategies For Global Flow Instability Analysis

A novel time-stepping shift-invert algorithm for linear stability analysis of laminar flows in complex geometries is presented. This method, based on a Krylov subspace iteration, enables the solution of complex non-symmetric eigenvalue problems in a matrix-free framework. Validations and comparisons to the classical exponential method have been performed in three different cases: (i) stenotic flow, (ii) backward-facing step and (iii) lid-driven swirling flow. Results show that this new approach speeds up the required Krylov subspace iterations and has the capability of converging to specific parts of the global spectrum. It is shown that, although the exponential method remains the method of choice if leading eigenvalues are sought, the performance of the present method could be dramatically improved with the use of a preconditioner. In addition, as opposed to other methods, this strategy can be directly applied to any time-stepper, regardless of the temporal or spatial discretization of the latter.