Distribution of the coal flow in the mill-duct system of the As Pontes Power Plant using CFD modeling

The efficiency of a Power Plant is affected by the distribution of the pulverized coal within the furnace. The coal, which is pulverized in the mills, is transported and distributed by the primary gas through the mill-ducts to the interior of the furnace. This is done with a double function: dry and enter the coal by different levels for optimizing the combustion in the sense that a complete combustion occurs with homogeneous heat fluxes to the walls. The mill-duct systems of a real Power Plant are very complex and they are not yet well understood. In particular, experimental data concerning the mass flows of coal to the different levels are very difficult to measure. CFD modeling can help to determine them. An Eulerian/Lagrangian approach is used due to the low solid–gas volume ratio.

Condensation in ducts

Phase changing flows are being considered for thermal management in space platforms. The resulting flow patterns are very complicated and extremely sensitive to gravity action. Concerning fluid flow in ducts, the available evidence indicates that although the pressure loss does not depend too much on the fluid flow pattern,the heat transfer (and resulting phase change) does. A simple exercise to illustrate this point is presented in this paper. It deals with condensing flow in straight circular cross-sectional ducts. Two extreme configurations are considered here, one corresponds to a stratified flow and the other to an annular flow. Both types of flow patterns have been extensively considered in the past and from this point of view almost nothing is new in the paper, but past results look conflictive and this could be due to the limitations and computational intricacies of the models used. Thus the problem has been reformulated from the onset and the results are presented as the evolution of the vapor quality (vapor to total mass flow rate) along the duct, in typical cases. The results presented here indicate that within the validity of the present models and the assumed ranges of mass flow rate, duct diameter, thermal conditions and fluid characteristics,the length of the ducts required to achieve complete condensation under zero gravity are an order of magnitude larger than in horizontal tubes under normal terrestrial conditions.

Static Pressure Impact on Aerodynamics of High Speed Railway Tunnels

A pressure wave is generated when a high speed train enters a tunnel. This wave travels along the tunnel back and forth, and is reflected at the irregularities of the tunnel duct (section changes, chimneys and tunnel ends). The pressure changes are associated to these waves can have an effect on passengers if the trains are not suitably sealed or pressurized. The intensity of the waves depends mainly on the train speed, and on the blockage ratio (train-section-to- tunnel-section area ratio). As the intensity of the waves is limited by regulations, and also by the effects on passengers and infrastructures, the sizing of the tunnel section area is largely influenced by the maximum train speed allowed in the tunnel. The aim of this study is to analyse the increase in cost in a tunnel due to the existence of this difference in ground level, and evaluate the increase of construction costs that this elevation might involve.

Diseño de laboratorio para la evaluación de silenciadores "in situ"

Se ha realizado el diseño de un sistema que permite realizar ensayos de silenciadores “in situ”. Para evaluar el comportamiento del sistema de ensayo de silenciadores se procede a caracterizar los paneles acústicos que son la base del sistema. De los paneles empleados en el sistema, se determinará por diferencia del nivel de presión sonora, el aislamiento a ruido aéreo de los mismos, partiendo del promedio de las medidas obtenidas en la sala emisora de la cámara reverberante con el material instalado y en la sala receptora. Se realizan distintas medidas de los niveles de presión sonora en sala emisora de la cámara reverberante y en la receptora así como del tiempo de reverberación con los paneles instalados en el hueco existente en el elemento de separación vertical de la cámara. Una vez ensayados los paneles, se ha procedido a medir los niveles de presión sonora que se obtienen antes y después de la interposición de distintos silenciadores en el sistema diseñado con el propósito de disponer de un laboratorio de medida de la atenuación de silenciadores. Para ello, se procede a efectuar el montaje, en la puerta sencilla de la cámara reverberante, de los componentes del sistema diseñado y se realizan mediciones de la atenuación que proporciona la colocación de un silenciador en el sistema y su posterior sustitución por un conducto. La medición de la atenuación del nivel de presión sonora que producen los distintos silenciadores se realiza por pérdidas por inserción, siguiendo las directrices de la Norma UNE-ISO 11820 y por el método de conductos forrados como cálculo teórico. ABSTRACT. A system has been designed for testing silencers “in situ”. In first place, to evaluate the behavior of the system in the test of silencers, it has been proceeded to customize the acoustic panels that are the basis of the system. The attenuation sound of the panels used in the system will be determined by the difference of sound pressure level. It will be made through the average of the measurements obtained in the source room of the reverberant chamber, the average of the measurements obtained in the receiving room, as well as the reverberation time, with the material installed in the hole of the walls. Once the panels are tested, and with the purpose of having a laboratory to measure the attenuation of silencers, the sound pressure levels has been measured before and after inserting the different silencers in the designed system. To obtain these measures, the components of the system designed have been installed in the hollow of the single door of the reverberant chamber and then the sound pressure level has been measured with a silencers first and after with a duct instead of the silencer. The measurement of the attenuation of the sound pressure level produced by different silencers has been made by insertion loss, following the 11820 UNE-ISO, as well as theoretical calculation has been made by the method of duct lined.

Analysis of air flow past and through the 2415-3S airfoil for an unmanned aerial vehicle with internal propulsion system

This paper deals with the prediction of velocity fields on the 2415-3S airfoil which will be used for an unmanned aerial vehicle with internal propulsion system and in this way analyze the air flow through an internal duct of the airfoil using computational fluid dynamics. The main objective is to evaluate the effect of the internal air flow past the airfoil and how this affects the aerodynamic performance by means of lift and drag forces. For this purpose, three different designs of the internal duct were studied; starting from the base 2415-3S airfoil developed in previous investigation, basing on the hypothesis of decreasing the flow separation produced when the propulsive airflow merges the external flow, and in this way obtaining the best configuration. For that purpose, an exhaustive study of the mesh sensitivity was performed. It was used a non-structured mesh since the computational domain is three-dimensional and complex. The selected mesh contains approximately 12.5 million elements. Both the computational domain and the numerical solution were made with commercial CAD and CFD software, respectively. Air, incompressible and steady was analyzed. The boundary conditions are in concordance with experimental setup in the AF 6109 wind tunnel. The k-e model is utilized to describe the turbulent flow process as followed in references. Results allowed obtaining velocity contours as well as lift and drag coefficients and also the location of separation and reattachment regions in some cases for zero degrees of angle of attack on the internal and external surfaces of the airfoil. Finally, the selection of the configuration with the best aerodynamic performance was made, selecting the option without curved baffles.

Numerical analysis of air flow past the 2415-3S airfoil for an unmanned aerial vehicle with internal propulsion system

This paper deals with the prediction of pressure and velocity fields on the 2415-3S airfoil which will be used for and unmanned aerial vehicle with internal propulsion system and in this way analyze the air flow through an internal duct of the airfoil using computational fluid dynamics. The main objective is to evaluate the effect of the internal air flow past the airfoil and how this affects the aerodynamic performance by means of lift and drag forces. For this purpose, three different designs of the internal duct were studied; starting from the base 2415-3S airfoil developed in previous investigation, basing on the hypothesis of decreasing the flow separation produced when the propulsive airflow merges the external flow, and in this way obtaining the best configuration. For that purpose, an exhaustive study of the mesh sensitivity was performed. It was used a non-structured mesh since the computational domain is tridimensional and complex. The selected mesh contains approximately 12.5 million elements. Both the computational domain and the numerical solution were made with commercial CAD and CFD software respectively. Air, incompressible and steady was analyzed. The boundary conditions are in concordance with experimental setup in the AF 6109 wind tunnel. The k-ε model is utilized to describe the turbulent flow process as followed in references. Results allowed obtaining pressure and velocity contours as well as lift and drag coefficients and also the location of separation and reattachment regions in some cases for zero degrees of angle of attack on the internal and external surfaces of the airfoil. Finally, the selection of the configuration with the best aerodynamic performance was made, selecting the option without curved baffles.