Computationally efficient method to construct scar functions

Phys. Rev. E 85, 026214-026219 (2012) Desarrollo de un nuevo y eficiente método para la construcción de funciones de scar a lo largo de las órtbitas periódicas inestables de sistemas clásicamente caóticos

Estudio de la estructura de autofunciones de sistemas caóticos en una base de funciones de scar

El problema central que aborda esta tesis doctoral es el estudio de la correspondencia entre la mecanica clasica y la mecanica cuantica en sistemas hamiltonianos clasicamente caoticos, tema que se enmarca dentro del llamado caos cuantico. En concreto, en este trabajo proponemos un nuevo y efectivo metodo para calcular las autofunciones de sistemas caoticos usando una base de funciones de scar. Dichas funciones de scar juegan un papel fundamental en el estudio de las manifestaciones cuanticas del caos, ya que se trata de funciones de onda semiclasicas con una dispersion muy peque~na y localizadas a lo largo de las variedades invariantes de las orbitas periodicas inestables del sistema que conforman la estructura organizativa del caos clasico. El metodo de calculo desarrollado se ha denominado Metodo de Gram- Schmidt Selectivo (MGSS), dado que construye la base haciendo uso del metodo de Gram{Schmidt convencional pero teniendo en cuenta, ademas, la dispersi on de las funciones de scar y la longitud de la orbita periodica a lo largo de la cual se localizan. El MGSS nos ha permitido calcular con gran precision las 2400 autofunciones con menor energa de un oscilador cuartico altamente caotico con dos grados de libertad acoplados, as como autofunciones muy excitadas en una ventana de energa, utilizando en ambos casos una base mucho mas eciente que las descritas en la literatura. Ademas, hemos empleado el MGSS para calcular las autofunciones del sistema molecular LiNC/LiCN, que presenta un espacio de fases con zonas de regularidad y con regiones en las que el movimiento es altamente caotico; en este ultimo sistema, hemos calculado de forma muy eciente las autofunciones asociadas a las primeras 66 energas. Finalmente, hemos propuesto un metodo perturbativo para calcular velocidades de reaccion en sistemas abiertos descritos por potenciales anarmonicos. Con este metodo, hemos calculado la velocidad de reaccion de distintos potenciales de uno y dos grados de libertad, as como la velocidad de isomerizacion del sistema molecular LiNC/LiCN, tanto sometido a un ruido blanco (sin correlaciones) como en presencia de un ba~no de atomos de argon, lo que constituye un entorno con correlaciones. El metodo desarrollado es independiente de la supercie divisoria y nos ha permitido obtener correcciones analticas a la famosa formula de Kramers, lo que posibilita el calculo exacto de velocidades de reaccion en potenciales anarmonicos que interaccionan con el entorno.

Do the spatial characteristics of myocardial scar tissue determine the risk of ventricular arrhythmias?

Sudden cardiac death is one of the main causes of mortality in patients with structural heart disease. Although an implantable cardioverter de?brillator signi?cantly reduces the mortality rate, many patients never receive a shock. Identi?cation of high-risk patients would reduce the costs associated with this therapy and prevent the deleterious effect of inappropriate discharges. As scar tissue is the substrate of ventricular arrhythmias in patients with structural heart disease, scar characterization could allow strati?cation of the risk. The objective of this article is to review the role of scar characteristics in the pathogenesis of ventricular arrhythmias in patients with structural heart disease.

¡Bravo, Óscar, bravo!

Artículo publicado en el periódico El Mundo el 7 de diciembre de 2012.

Experimental and numerical assessment of the aeroelastic stability of blade pair packages

The stabilizing effect of grouping rotor blades in pairs has been assessed both, numerically and experimentally. The bending and torsion modes of a low aspect ratio high speed turbine cascade tested in the non-rotating test facility at EPFL (Ecole Polytechnique Fédérale de Lausanne) have been chosen as the case study. The controlled vibration of 20 blades in travelling wave form was performed by means of an electromagnetic excitation system, enabling the adjustement of the vibration amplitude and inter blade phase at a given frequency. Unsteady pressure transducers located along the blade mid-section were used to obtain the modulus and phase of the unsteady pressure caused by the airfoil motion. The stabilizing effect of the torsion mode was clearly observed both in the experiments and the simulations, however the effect of grouping the blades in pairs in the minimum damping at the tested frequency was marginal in the bending mode. A numerical tool was validated using the available experimental data and then used to extend the results at lower and more relevant reduced frequencies. It is shown that the stabilizing effect exists for the bending and torsion modes in the frequency range typical of low-pressure turbines. It is concluded that the stabilizing effect of this configuration is due to the shielding effect of the pressure side of the airfoil that defines the passage of the pair on the suction side of the same passage, since the relative motion between both is null. This effect is observed both in the experiments and simulations.

Pararotor dynamics: center of mass displacement from the blade plane—analytical approach

The pararotor is a biology-inspired decelerator device based on the autorotation of a rotary wing whose main purpose is to guide a load descent into a certain atmosphere. This paper focuses on a practical approach to the general dynamic stability of a pararotor whose center of mass is displaced from the blade plane. The analytical study departs from the motion equations of pararotor flight, considering the center of mass displacement from the blade plane, studied over a number of simplifying hypotheses that allows determining the most important influences to flight behavior near equilibrium. Two practical indexes are developed to characterize the stability of a pararotor in terms of geometry, inertia, and the aerodynamic characteristics of the device. Based on these two parameters, a stability diagram can be defined upon which stability regions can be identified. It was concluded that the ability to reach stability conditions depends mainly on a limited number of parameters associated with the pararotor configuration: the relationship between moments of inertia, the position of the blades, the planform shape (associated with the blade aerodynamic coefficients and blade area), and the vertical distance between the center of mass and the blade plane. These parameters can be evaluated by computing practical indexes to determine stability behavior.

An engineering modification of the blade element momentum combination applicable in vertical descent flight :fundamentals and validation

An engineering modification of blade element/momentum theory is applied to describe the vertical autorotation of helicopter rotors. A full non‐linear aerodynamic model is considered for the airfoils, taking into account the dependence of lift and drag coefficients on both the angle of attack and the Reynolds number. The proposed model, which has been validated in previous work, has allowed the identification of different autorotation modes, which depend on the descent velocity and the twist of the rotor blades. These modes present different radial distributions of driven and driving blade regions, as well as different radial upwash/downwash patterns. The number of blade sections with zero tangential force, the existence of a downwash region in the rotor disk, the stability of the autorotation state, and the overall rotor autorotation efficiency, are all analyzed in terms of the flight velocity and the characteristics of the rotor. It is shown that, in vertical autorotation, larger blade twist leads to smaller values of descent velocity for a given thrust generated by the rotor in the autorotational state.

An engineering modification of the blade element momentum equation for vertical descent : an autoration case study

An engineering modification of blade element/momentum theory is applied to describe the vertical autorotation of helicopter rotors. A full non-linear aerodynamic model is considered for the airfoils, taking into account the dependence of lift and drag coefficients on both the angle of attack and the Reynolds number. The proposed model, which has been validated in previous work, has allowed the identification of different autorotation modes, which depend on the descent velocity and the twist of the rotor blades. These modes present different radial distributions of driven and driving blade regions, as well as different radial upwash/downwash patterns. The number of blade sections with zero tangential force, the existence of a downwash region in the rotor disk, the stability of the autorotation state, and the overall rotor autorotation efficiency, are all analyzed in terms of the flight velocity and the characteristics of the rotor. It is shown that, in vertical autorotation, larger blade twist leads to smaller values of descent velocity for a given thrust generated by the rotor in the autorotational state.

Blade-wake interactions in cross-flow turbines

This paper presents analytical bounds for blade–wake interaction phenomenona occurring in rotating cross-flow turbines for wind and tidal energy generation (e.g. H rotors, Darrieus or vertical axis). Limiting cases are derived for one bladed turbines and extended to the more common three bladed configuration. Additionally, we present a classification of the blade–wake type of interactions in terms of limiting tip speed ratios. These bounds are validated using a high order h=p Discontinuous Galerkin solver with sliding meshes. This computational method enables highly accurate flow solutions and shows that the analytical bounds correspond to limiting blade-wake interactions in fully resolved flow simulations