Projeto e dimensionamento da tampa de ventilação de um motor elétrico

Nos dias de hoje a indústria tenta tornar-se cada vez mais competitiva baixando os custos de produção e aumentando a eficiência do produto. O presente trabalho visa desenvolver uma tampa de ventilação de um motor elétrico mais competitiva mas que cumpra com o desempenho mecânico e eficiência solicitados. Para tal, começou-se por analisar alguns motores elétricos e as suas aplicações. Seguidamente apresentam-se conceitos sobre aerodinâmica e processos de fabrico que permitem apoiar as opções tomadas ao longo do estudo. Após o fundamento teórico é apresentado todo o processo de desenvolvimento de uma nova peça. Recorrendo a softwares como o solidworks e Ansys, realizou-se uma análise analítica que permitiu validar as alterações propostas na tampa de ventilação. Foram, ainda, realizadas análises experimentais com o intuito de consolidar os resultados obtidos analiticamente e garantir que o componente cumpria os requisitos impostos por organizações internacionais ligadas à indústria do oil and gas. A primeira das análises experimentais realizada testa a capacidade do material resistir ao impacto de componentes de pequenas dimensões. Esta analise permitiu garantir a utilização da tampa de ventilação em todas as áreas sem limites de normalização. A segunda permite analisar experimentalmente as alterações de design assim como testar alguns trabalhos futuros. Esta análise permitiu definir se no novo projeto da tampa desenvolvido deveria comtemplar uma alteração do diâmetro da entrada de ar da tampa de ventilação. Como resultados aparecem as decisões tomadas na presente tese, assim como analisar as metas que foram atingidas e que melhorias se pretende atingir de futuro tentando visar novas metas. Os resultados obtidos permitiram definir uma nova tampa de ventilação com a nova que irá beneficiar a empresa na sua competitividade no mercado mantendo a performance do motor.

A method to correct the flow distortion of offshore wind data using CFD simulation and experimental wind tunnel tests

The assessment of wind energy resource for the development of deep offshore wind plants requires the use of every possible source of data and, in many cases, includes data gathered at meteorological stations installed at islands, islets or even oil platforms—all structures that interfere with, and change, the flow characteristics. This work aims to contribute to the evaluation of such changes in the flow by developing a correction methodology and applying it to the case of Berlenga island, Portugal. The study is performed using computational fluid dynamic simulations (CFD) validated by wind tunnel tests. In order to simulate the incoming offshore flow with CFD models a wind profile, unknown a priori, was established using observations from two coastal wind stations and a power law wind profile was fitted to the existing data (a=0.165). The results show that the resulting horizontal wind speed at 80 m above sea level is 16% lower than the wind speed at 80 m above the island for the dominant wind direction sector.

Memòria justificativa de l'estada de recerca

Estudi elaborat a partir d’una estada a l’Associação para o Desenvolvimento da Aerodinânica Industrial (ADAI) de la Universitat de Coimbra, Portugal, entre març i juliol de 2006. Aquesta disposa d'un laboratori d'assaigs i té medis suficients per a cremar de manera controlada parcel•les prèviament delimitades en terreny forestal. Això permet observar el fenomen dels incendis forestals a dues escales de treball diferents. L’objectiu ha estat l’obtenció de dades experimentals sobre la propagació de fronts de flames que avancen sobre combustible tractat amb retardants sota l’efecte del pendent o el vent. S’ha participat en proves experimentals de camp i se n’han realitzat dues en instal•lacions de laboratori en què l’efecte del pendent o de la velocitat del vent podia ser variat. Degut a l’elevat nombre de variables que entren en joc l’anàlisi acurada de les dades encara està en procés.

Developing discontinuous Galerkin methods for the resolution of the incompressible Navier-Stokes equations

Informe de investigación elaborado a partir de una estancia en el Laboratorio de Diseño Computacional en Aeroespacial en el Massachusetts Institute of Technology (MIT), Estados Unidos, entre noviembre de 2006 y agosto de 2007. La aerodinámica es una rama de la dinámica de fluidos referida al estudio de los movimientos de los líquidos o gases, cuya meta principal es predecir las fuerzas aerodinámicas en un avión o cualquier tipo de vehículo, incluyendo los automóviles. Las ecuaciones de Navier-Stokes representan un estado dinámico del equilibrio de las fuerzas que actúan en cualquier región dada del fluido. Son uno de los sistemas de ecuaciones más útiles porque describen la física de una gran cantidad de fenómenos como corrientes del océano, flujos alrededor de una superficie de sustentación, etc. En el contexto de una tesis doctoral, se está estudiando un flujo viscoso e incompresible, solucionando las ecuaciones de Navier- Stokes incompresibles de una manera eficiente. Durante la estancia en el MIT, se ha utilizado un método de Galerkin discontinuo para solucionar las ecuaciones de Navier-Stokes incompresibles usando, o bien un parámetro de penalti para asegurar la continuidad de los flujos entre elementos, o bien un método de Galerkin discontinuo compacto. Ambos métodos han dado buenos resultados y varios ejemplos numéricos se han simulado para validar el buen comportamiento de los métodos desarrollados. También se han estudiado elementos particulares, los elementos de Raviart y Thomas, que se podrían utilizar en una formulación mixta para obtener un algoritmo eficiente para solucionar problemas numéricos complejos.

Estudi de l’eficiència aerodinàmica de vehicles pesants de transport de passatgers

Estudi de l’eficiència aerodinàmica de les carrosseries de vehicles pesants de cara a reduir el consum de combustible en autocars de llarg trajecte. L’estudi es basa en tres aspectes: validació del programa de simulació, estudi aerodinàmic de diferents carrosseries d’autocar de mercat i estudi aerodinàmic de diferents complements

Millora aerodinàmica de la nova carrosseria del vehicle l'Àliga. Estudis dels efectes de la rugositat i l'inserció d'apèndixs aerodinàmics

L' objectiu d' aquest estudi és intentar millorar l' aerodinàmica de la nova carrosseria del vehicle de baix consum de la UdG,l' Àliga, a través de programes informàtics de CFD.Des de fa uns anys l' Escola Politècnica Superior de la Universitat de Girona participa a l' Eco Shell Marathon, mirant d' assolir els millors resultats possibles.El nom del vehicle utilitzat per aquesta carrera és l' Àliga.Aquest projecte parteix dels resultats obtinguts al Projece fi de carrera d' en Daniel Vilavedra Vilà (2006):"Redisseny aerodinàmic de la carrosseria del vehicle de baix consum Àliga"

Estudi de l’eficiència aerodinàmica de vehicles pesants de transport de passatgers

Estudi de l’eficiència aerodinàmica de les carrosseries de vehicles pesants de cara a reduir el consum de combustible en autocars de llarg trajecte. L’estudi es basa en tres aspectes: validació del programa de simulació, estudi aerodinàmic de diferents carrosseries d’autocar de mercat i estudi aerodinàmic de diferents complements

Estudi de la influència del vent en l’estabilitat de vehicles pesants de transport de viatgers.

Investigacions recents revelen com l’acció del vent lateral és un efecte molt important en bona part dels accidents ocorreguts en vehicles pesants de transport per carretera. És per això que el perfil aerodinàmic del vehicle esdevé determinant en l’avaluació de les forces laterals que hi actuen.El present projecte té per objecte determinar les forces laterals que s’exerceixen en vehicles pesants de transport de passatgers degut a l’acció del vent i investigar-ne la seva perillositat. Per fer-ho s’utilitzen models numèrics de dinàmica de fluids i, per diferents velocitats del vehicle, es simulen vents amb diferent intensitat i direcció. D’aquí es determinen unes condicions de perillositat en funció, entre d’altres variables, de l’angle d’incidència del vent i de la seva velocitat

Molecular Physics of Elementary Processes relevant to Hypersonics: atom-molecule, molecule-molecule and atom-surface processes.

In the present chapter some prototype gas and gas-surface processes occurring within the hypersonic flow layer surrounding spacecrafts at planetary entry are discussed. The discussion is based on microscopic dynamical calculations of the detailed cross sections and rate coefficients performed using classical mechanics treatments for atoms, molecules and surfaces. Such treatment allows the evaluation of the efficiency of thermal processes (both at equilibrium and nonequilibrium distributions) based on state-to-state and state specific calculations properly averaged over the population of the initial states. The dependence of the efficiency of the considered processes on the initial partitioning of energy among the various degrees of freedom is discussed.

Estudi i simulació aerodinàmica amb programari de dinàmica de fluids computacional (CFD) en un model bàsic de vehicle de competició de la categoria CM (curses de muntanya)

Aquest projecte té com a objectiu la simulació numérica de la carrosseria d’ un vehicle de curses de muntanya de categoria CM

Ballistisen simuloinnin liikeidean kehittämismahdollisuudet

Asevaikutusta laukaisusta kohteeseen simuloiva integroitu laskentaketju koostuu sisä-, ulko- ja maaliballistiikan malleista. Ulkoballistiikka kattaa laskentamallit radanlaskennan, sääkorjauksen ja ammusaerodynamiikan alueilla. Graafisella käyttöliittymällä toteutetulla, fysikaalisesti tarkkaan mallinnukseen perustuvalla ja kokonaisuuden kattavalla laskentajärjestelmällä on kasvavaa tarvetta teknisiä ja koulutuksellisia tarkoituksia varten. Erikoisesti, jos laskentaketjuun lisätään räjähdysvaikutuksen mallintaminen, voidaan simuloida asejärjestelmien vaikutusta kohteessa käyttäjien arvostamalla tavalla. Tietointensiiviset ballistiikan laskentamallit ovat välttämättömiä työkaluja teknisen suunnitteluosaamisen kattamiseksi ja kilpailuedun luomiseksi verkostoituneessa yritysympäristössä. Yliopistotutkimuksen tuottamien laskennallisten menetelmien hyötykäyttö yritysten suunnittelujärjestelmissä syventää teknistä osaamista, jolla on myös henkilöstöä motivoiva vaikutus teknisesti vaikeutuvilla markkinoilla. Työssä arvioidaan toimialaa analysoimalla eri käyttötarpeita samoille tietokantoihin tukeutuville laskentamalleille. Tarkastellaan teknisiä perusteita, käyttöympäristöjä ja markkinoita liiketoimintamahdollisuuksien tunnistamiseksi. Työn tuloksena syvennetään näkemystä ydinosaamisista ja visioidaan liikeidean erottumista kilpailijoista, markkinoita ja sen kehittämistä.

On the development of an unstructured grid solver for inert and reactive high speed flow simulations

An unstructured grid Euler solver for reactive compressible flow applications is presented. The method is implemented in a cell centered, finite volume context for unstructured triangular grids. Three different schemes for spatial discretization are implemented and analyzed. Time march is implemented in a time-split fashion with independent integrators for the flow and chemistry equations. The capability implemented is tested for inert flows in a hypersonic inlet and for inert and reactive supersonic flows over a 2-D wedge. The results of the different schemes are compared with each other and with independent calculations using a structured grid code. The strengths and the possible weaknesses of the proposed methods are discussed.

Solution of aerospace problems using structured and unstructured strategies

Products developed at industries, institutes and research centers are expected to have high level of quality and performance, having a minimum waste, which require efficient and robust tools to numerically simulate stringent project conditions with great reliability. In this context, Computational Fluid Dynamics (CFD) plays an important role and the present work shows two numerical algorithms that are used in the CFD community to solve the Euler and Navier-Stokes equations applied to typical aerospace and aeronautical problems. Particularly, unstructured discretization of the spatial domain has gained special attention by the international community due to its ease in discretizing complex spatial domains. This work has the main objective of illustrating some advantages and disadvantages of numerical algorithms using structured and unstructured spatial discretization of the flow governing equations. Numerical methods include a finite volume formulation and the Euler and Navier-Stokes equations are applied to solve a transonic nozzle problem, a low supersonic airfoil problem and a hypersonic inlet problem. In a structured context, these problems are solved using MacCormack’s implicit algorithm with Steger and Warming’s flux vector splitting technique, while, in an unstructured context, Jameson and Mavriplis’ explicit algorithm is used. Convergence acceleration is obtained using a spatially variable time stepping procedure.

Panel Method Formulation for Oscillating Airfoils in Sonic Flow

The mathematical model for two-dimensional unsteady sonic flow, based on the classical diffusion equation with imaginary coefficient, is presented and discussed. The main purpose is to develop a rigorous formulation in order to bring into light the correspondence between the sonic, supersonic and subsonic panel method theory. Source and doublet integrals are obtained and Laplace transformation demonstrates that, in fact, the source integral is the solution of the doublet integral equation. It is shown that the doublet-only formulation reduces to a Volterra integral equation of the first kind and a numerical method is proposed in order to solve it. To the authors' knowledge this is the first reported solution to the unsteady sonic thin airfoil problem through the use of doublet singularities. Comparisons with the source-only formulation are shown for the problem of a flat plate in combined harmonic heaving and pitching motion.

Non-Linear Unsteady Aerodynamic Response Approximation Using Multi-Layer Functionals

Non-linear functional representation of the aerodynamic response provides a convenient mathematical model for motion-induced unsteady transonic aerodynamic loads response, that accounts for both complex non-linearities and time-history effects. A recent development, based on functional approximation theory, has established a novel functional form; namely, the multi-layer functional. For a large class of non-linear dynamic systems, such multi-layer functional representations can be realised via finite impulse response (FIR) neural networks. Identification of an appropriate FIR neural network model is facilitated by means of a supervised training process in which a limited sample of system input-output data sets is presented to the temporal neural network. The present work describes a procedure for the systematic identification of parameterised neural network models of motion-induced unsteady transonic aerodynamic loads response. The training process is based on a conventional genetic algorithm to optimise the network architecture, combined with a simplified random search algorithm to update weight and bias values. Application of the scheme to representative transonic aerodynamic loads response data for a bidimensional airfoil executing finite-amplitude motion in transonic flow is used to demonstrate the feasibility of the approach. The approach is shown to furnish a satisfactory generalisation property to different motion histories over a range of Mach numbers in the transonic regime.