Submitted by ROBERTO OUTA null (roberto.outa@gmail.com) on 2017-11-23T13:24:39Z No. of bitstreams: 1 Tese Doutorado Roberto Outa 23_11_2017.pdf: 8826970 bytes, checksum: 2d87ce6b0e50b1304328308f0df4e3bb (MD5) / Submitted by ROBERTO Outa (roberto.outa@gmail.com) on 2017-11-23T13:34:43Z No. of bitstreams: 1 Tese Doutorado Roberto Outa 23_11_2017.pdf: 8826970 bytes, checksum: 2d87ce6b0e50b1304328308f0df4e3bb (MD5) / Submitted by ROBERTO OUTA (roberto.outa@gmail.com) on 2017-11-23T17:24:54Z No. of bitstreams: 1 Tese Doutorado Roberto Outa 23_11_2017.pdf: 8826970 bytes, checksum: 2d87ce6b0e50b1304328308f0df4e3bb (MD5) / Submitted by ROBERTO OUTA (roberto.outa@gmail.com) on 2017-11-23T17:29:02Z No. of bitstreams: 1 Tese Doutorado Roberto Outa 23_11_2017.pdf: 8826970 bytes, checksum: 2d87ce6b0e50b1304328308f0df4e3bb (MD5) / Submitted by ROBERTO OUTA (roberto.outa@gmail.com) on 2017-11-24T12:05:25Z No. of bitstreams: 1 Tese Doutorado Roberto Outa 23_11_2017.pdf: 8826970 bytes, checksum: 2d87ce6b0e50b1304328308f0df4e3bb (MD5) / Submitted by ROBERTO OUTA (roberto.outa@gmail.com) on 2017-11-24T12:39:45Z No. of bitstreams: 1 Tese Doutorado Roberto Outa 23_11_2017.pdf: 8826970 bytes, checksum: 2d87ce6b0e50b1304328308f0df4e3bb (MD5) / Submitted by ROBERTO OUTA (roberto.outa@gmail.com) on 2017-11-24T16:47:39Z No. of bitstreams: 1 Tese Doutorado Roberto Outa 23_11_2017.pdf: 8826970 bytes, checksum: 2d87ce6b0e50b1304328308f0df4e3bb (MD5) / Submitted by ROBERTO OUTA (roberto.outa@gmail.com) on 2017-11-24T17:31:21Z No. of bitstreams: 1 Tese Doutorado Roberto Outa 23_11_2017.pdf: 8826970 bytes, checksum: 2d87ce6b0e50b1304328308f0df4e3bb (MD5) / Submitted by ROBERTO OUTA (roberto.outa@gmail.com) on 2017-11-27T11:40:49Z No. of bitstreams: 1 Tese Doutorado Roberto Outa 23_11_2017.pdf: 8826970 bytes, checksum: 2d87ce6b0e50b1304328308f0df4e3bb (MD5) / Submitted by ROBERTO OUTA (roberto.outa@gmail.com) on 2017-11-27T12:31:51Z No. of bitstreams: 1 Tese Doutorado Roberto Outa 23_11_2017.pdf: 8826970 bytes, checksum: 2d87ce6b0e50b1304328308f0df4e3bb (MD5) / Submitted by ROBERTO OUTA (roberto.outa@gmail.com) on 2017-11-27T13:03:16Z No. of bitstreams: 1 Tese Doutorado Roberto Outa 23_11_2017.pdf: 8826970 bytes, checksum: 2d87ce6b0e50b1304328308f0df4e3bb (MD5) / Submitted by ROBERTO OUTA (roberto.outa@gmail.com) on 2017-11-27T18:08:08Z No. of bitstreams: 1 Tese Doutorado Roberto Outa 23_11_2017.pdf: 8826970 bytes, checksum: 2d87ce6b0e50b1304328308f0df4e3bb (MD5) / Submitted by ROBERTO OUTA (roberto.outa@gmail.com) on 2017-11-28T12:13:08Z No. of bitstreams: 1 Tese Doutorado Roberto Outa 23_11_2017.pdf: 8826970 bytes, checksum: 2d87ce6b0e50b1304328308f0df4e3bb (MD5) / Submitted by ROBERTO OUTA (roberto.outa@gmail.com) on 2017-11-28T14:22:47Z No. of bitstreams: 1 Tese Doutorado Roberto Outa 23_11_2017.pdf: 8826970 bytes, checksum: 2d87ce6b0e50b1304328308f0df4e3bb (MD5) / Submitted by ROBERTO OUTA (roberto.outa@gmail.com) on 2017-11-28T14:31:57Z No. of bitstreams: 1 Tese Doutorado Roberto Outa 23_11_2017.pdf: 8826970 bytes, checksum: 2d87ce6b0e50b1304328308f0df4e3bb (MD5) / Submitted by ROBERTO OUTA (roberto.outa@gmail.com) on 2017-11-28T14:37:45Z No. of bitstreams: 1 Tese Doutorado Roberto Outa 23_11_2017.pdf: 8826970 bytes, checksum: 2d87ce6b0e50b1304328308f0df4e3bb (MD5) / Submitted by ROBERTO OUTA (roberto.outa@gmail.com) on 2017-11-28T19:04:28Z No. of bitstreams: 1 Tese Doutorado Roberto Outa 23_11_2017.pdf: 8826970 bytes, checksum: 2d87ce6b0e50b1304328308f0df4e3bb (MD5) / Submitted by ROBERTO OUTA (roberto.outa@gmail.com) on 2017-11-30T18:58:21Z No. of bitstreams: 1 Tese Doutorado Roberto Outa 23_11_2017.pdf: 8826970 bytes, checksum: 2d87ce6b0e50b1304328308f0df4e3bb (MD5) / Submitted by ROBERTO OUTA (roberto.outa@gmail.com) on 2017-12-04T14:43:24Z No. of bitstreams: 1 Tese Doutorado Roberto Outa 23_11_2017.pdf: 8826970 bytes, checksum: 2d87ce6b0e50b1304328308f0df4e3bb (MD5) / Submitted by ROBERTO OUTA (roberto.outa@gmail.com) on 2017-12-05T14:11:15Z No. of bitstreams: 1 Tese Doutorado Roberto Outa 23_11_2017.pdf: 8826970 bytes, checksum: 2d87ce6b0e50b1304328308f0df4e3bb (MD5) / Approved for entry into archive by Roberta Honorato Goria null (robertacgb@reitoria.unesp.br) on 2017-12-06T18:19:51Z (GMT) No. of bitstreams: 1 outa_r_dr_ilha.pdf: 8826970 bytes, checksum: 2d87ce6b0e50b1304328308f0df4e3bb (MD5) / Made available in DSpace on 2017-12-06T18:19:51Z (GMT). No. of bitstreams: 1 outa_r_dr_ilha.pdf: 8826970 bytes, checksum: 2d87ce6b0e50b1304328308f0df4e3bb (MD5) Previous issue date: 2017-10-27 / O objetivo deste trabalho é a elaboração de um controlador linear ótimo, que possa reduzir um sinal caótico do rotor dinâmico, em um sinal controlado. Para se obter o resultado esperado foi necessário desenvolver atividades ligadas à caracterização do experimento; análise de estabilidade pelo método de Lyapunov; aplicação da função de Lyapunov; análise da sensibilidade das condições iniciais utilizando o expoente de Lyapunov; desenvolvimento do projeto do controle ótimo linear. O resultado final mostra o desempenho da aplicação do controle linear ótimo no sinal caótico, cujo sinal foi reduzido para um comportamento estável e controlado. / The aim of this work is the elaboration of an optimal linear controller that can reduce a chaotic dynamic rotor signal in a controlled signal. To obtain the expected result, it was necessary to develop activities related to the characterization of the experiment; stability analysis by the Lyapunov method; application of the Lyapunov function; sensitivity analysis of the initial conditions by the Lyapunov exponent; development of linear optimum control. The result shows the performance of the optimal linear control in the chaotic signal, whose signal was reduced to a stable and controlled behavior.

Orientador: Fábio Roberto Chavarette / Resumo: O objetivo deste trabalho é a elaboração de um controlador linear ótimo, que possa reduzir um sinal caótico do rotor dinâmico, em um sinal controlado. Para se obter o resultado esperado foi necessário desenvolver atividades ligadas à caracterização do experimento; análise de estabilidade pelo método de Lyapunov; aplicação da função de Lyapunov; análise da sensibilidade das condições iniciais utilizando o expoente de Lyapunov; desenvolvimento do projeto do controle ótimo linear. O resultado final mostra o desempenho da aplicação do controle linear ótimo no sinal caótico, cujo sinal foi reduzido para um comportamento estável e controlado. / Abstract: The aim of this work is the elaboration of an optimal linear controller that can reduce a chaotic dynamic rotor signal in a controlled signal. To obtain the expected result, it was necessary to develop activities related to the characterization of the experiment; stability analysis by the Lyapunov method; application of the Lyapunov function; sensitivity analysis of the initial conditions by the Lyapunov exponent; development of linear optimum control. The result shows the performance of the optimal linear control in the chaotic signal, whose signal was reduced to a stable and controlled behavior. / Doutor

The aerodynamic integration of an aero-engine intake system with the airframe can pose some notable challenges. This is particularly so for many military air- craft and is likely to become a more pressing issue for both new military systems with highly embedded engines as well as for novel civil aircraft configurations. During the late 1960s with the advent of turbo-fan engines, industry became in- creasingly aware of issues which arise due to inlet total pressure distortion. Since then, inlet-engine compatibility assessments have become a key aspect of any new development. In addition to total temperature and total pressure distortions, flow angularity and the associated swirl distortion are also known to be of notable con- cern. The importance of developing a rigorous methodology to understand the effects of swirl distortion on turbo-machinery has also become one of the major concerns of current design programmes. The goal of this doctoral research was to further the current knowledge on swirl distortion, and its adverse effects on engine performance, focusing on the turbo-machinery components (i.e. fans or compressors). This was achieved by looking into appropriate swirl flow descriptors and by correlating them against the compressor performance parameters (e.g loss in stability pressure ratios). To that end, a number of high-fidelity three-dimensional Computational Fluid Dynamics (CFD) models have been developed using two sets of transonic rotors (i.e. NASA Rotor 67 and 37), and a stator (NASA Stator 67B). For the numerical purpose, a boundary condition methodology for the definition of swirl distortion patterns at the inlet has been developed. Various swirl distortion numerical parametric studies have been performed using the modelled rotor configurations. Two types of swirl distortion pattern were investigated in the research, i.e. the pure bulk swirl and the tightly-wound vortex. Numerical simulations suggested that the vortex core location, polarity, size and strength greatly affect the compressor performance. The bulk swirl simula- tions also showed the dependency on swirl strength and polarity. This empha- sized the importance of quantifying these swirl components in the flow distortion descriptors. For this, a methodology have been developed for the inlet-engine compatibility assessment using different types of flow descriptors. A number of correlations have been proposed for the two types of swirl distortion investigated in the study.

Submitted by Maria Suzana Diniz (msuzanad@hotmail.com) on 2015-11-11T15:24:04Z No. of bitstreams: 1 arquivototal.pdf: 2659414 bytes, checksum: daffe4d3b79a46f98678d09a7952e81b (MD5) / Made available in DSpace on 2015-11-11T15:24:04Z (GMT). No. of bitstreams: 1 arquivototal.pdf: 2659414 bytes, checksum: daffe4d3b79a46f98678d09a7952e81b (MD5) Previous issue date: 2015-02-26 / Coordenação de Aperfeiçoamento de Pessoal de Nível Superior - CAPES / In this work, will be characterized two types of adsorptive wheels, an active effect and the other passive effect, known respectively as desiccant wheel and enthalpy wheel. These devices are used to compose the climatization adsorption systems as a means of promoting the dehumidification of air using the adsorption phenomenon that occurs in their adsorptive matrices. This phenomenon involves both the mass transfer and the heat, its cycles are defined by two processes taking place simultaneously, the adsorption and desorption. In the study, the characterization will boil down to assess the equipment in different working conditions with the main objective to achieve better dehumidification of air using the least amount of energy possible. Procedures were used for low air flow rates set in three categories: the process flow, which is the airflow to be treated, or dehumidified, a regeneration flow, which is the air stream in countercurrent flow desiccant rotor with process flow will serve as a means of maintaining the adsorptive cycle always performing heat exchange and mass, and the return flow, which flow against the enthalpy rotor will also serve as a means of promoting the dehumidification of process air. In the regeneration flow rates will be assessed the effects of low temperature heating and in both wheels will be evaluated the effects of different rotational speeds. Will also take place, procedures in order to verify the possibility of the wheel enthalpy work as a wheel desiccant . The findings contributed significantly to the climate control by adsorption systems is taken increasingly as a viable alternative to replacing conventional cooling. / No presente trabalho foram caracterizados dois tipos de rotores adsortivos, um de efeito ativo e outro de efeito passivo, conhecidos respectivamente como rotor dessecante e rotor entálpico. Esses equipamentos são usados para compor os sistemas de climatização por adsorção como meio de promover a desumidificação do ar usando o fenômeno da adsorção que ocorre em suas matrizes adsortivas. Esse fenômeno envolve tanto a transferência de massa quanto a de calor, seus ciclos são definidos por dois processos que ocorrem simultaneamente, a adsorção e a dessorção. No estudo, a caracterização se resume em avaliar os equipamentos em diferentes condições de trabalho tendo como principal objetivo alcançar a melhor desumidificação do ar usando a menor quantidade de energia possível. Durante os procedimentos foram usadas baixas vazões de ar definidas em três categorias: a vazão de processo, que é a corrente de ar a ser tratada, ou seja, desumidificada, a vazão de regeneração, que é a corrente de ar que em contra fluxo no rotor dessecante com a vazão de processo servirá como meio de manter o ciclo adsortivo sempre realizando as trocas de calor e massa, e a vazão de retorno, que em contra fluxo no rotor entálpico servirá também como meio de promover a desumidificação do ar de processo. Nas vazões de regeneração foram avaliados os efeitos de baixas temperaturas de aquecimento e em ambos os rotores foram avaliados os efeitos de diferentes rotações. Foram realizados também, procedimentos com o intuito de verificar a possibilidade de o rotor entálpico trabalhar como rotor dessecante. Os resultados desse trabalho contribuíram significativamente para que os sistemas de climatização por adsorção seja tido cada vez como uma alternativa viável à substituição da refrigeração convencional.

Made available in DSpace on 2016-12-12T17:38:36Z (GMT). No. of bitstreams: 1 rafael Campos resumo.pdf: 28958 bytes, checksum: c0306d4f10c2c1dab1c5e8750f4a0ea1 (MD5) Previous issue date: 2008-07-18 / Coordenação de Aperfeiçoamento de Pessoal de Nível Superior / The objective of this work is to study the rotor flux vector control applied to a single-phase induction motor drive. Initially, a mathematical model of the motor will be derived. The motor equations will be transformed to the stationary reference frame so that the angular dependency due to the asymmetry of the motor variables is eliminated. Then is discussed that single-phase induction motor can be viewed as a two-phase system. A mathematical model to derive the motor parameters is presented. The next step is to analyze the rotor flux vector control, pointing out the need for a symmetry transformation of the motor parameters. Two control methods are presented: direct rotor flux control and indirect rotor flux control. Theses control methods are validated through numerical simulations. Experimental analyses making use of a digital signal processor are carried out. The results obtained show the good dynamic response when the vector control method is applied to a single-phase induction motor drive system. / Este trabalho tem por objetivo estudar o acionamento do motor de indução utilizando o método de controle vetorial por fluxo de rotor. Inicialmente, desenvolvido o modelo matemático do motor de indução monofásico transformado o eixo estacionário para que seja eliminada a dependência angular das variáveis do devido à assimetria dos parâmetros do motor. É observado que o motor monofásico pode ser apresentado em configuração bifásica. Em seguida, um estudo de netrização do motor é realizado. O controle vetorial é analisado na seqüência, observando a necessidade de simetria dos parâmetros do motor para que haja um controle o do motor. São considerados dois métodos: controle direto do fluxo de rotor e indireto do fluxo de rotor. Analisa-se, também, o comportamento do controle de simulações numéricas Na seqüência,implementa-se experimentalmente o controle utilizando um processador digital de sinais. Os resultados obtidos mostram que o estudado ao ser aplicado ao motor de indução monofásico apresenta uma boa ta dinâmica para o sistema, tanto para método direto quanto para o método indireto.

L’introduction de fuselages et de pales de plus en plus légers durant le développement des nouveaux hélicoptères, combinée à une puissance disponible augmentée peut donner lieu à des couplages rotor/structure d’un nouveau genre. Ces instabilités complexes apparaissent à des fréquences plus élevées que les couplages connus et étudiés tels que les résonances sol et air, et impliquent des modes de pale souple, des modes de structure, et des phénomènes aérodynamiques. Des codes de calcul multi-corps aéromécaniques tels que HOST sont capables de déterminer la stabilité de l’hélicoptère, mais sont difficilement modifiables et manipulables. Des modèles analytiques existent également pour les instabilités maîtrisées citées précédemment, mais n’ont pas les capacités de modélisation nécessaires à la prédiction de ces couplages haute fréquence. Ce travail de thèse se concentre sur le développement d’un modèle semi-analytique, capable de prédire la stabilité de l’hélicoptère vis-à-vis de ces phénomènes. Cette approche est différente de l’approche multi-corps et a un double avantage car elle permet des études paramétriques rapides et une analyse terme à terme des équations de la dynamique de l’hélicoptère. Ce modèle a été validé à l’aide de HOST et le mécanisme de l'instabilité a été détaillé. Enfin, l’influence des paramètres de rotor, de structure, et de vol a été évaluée et les considérations architecturales pour éviter l'apparition de tels phénomènes sont présentées. / The introduction of lightweight fuselages and blades during new developments, combined with an increased available power, may lead to the triggering of a new kind of rotor/structure coupling. These complex instabilities appear at higher frequencies than known and studied couplings, such as ground and air resonance, and involve elastic blade modes, structure modes, and aerodynamic phenomena. Comprehensive analysis codes, like HOST, are able to determine the helicopter stability but can hardly be tweaked and handled. Rotor/structure coupling analytical models also exist for ground and air resonance, but do not have the modeling capabilities required to predict these high frequency couplings. This research work focuses on the development of a semi-analytical model, able to predict the helicopter stability with respect to these phenomena. This approach has a two-fold advantage since fast parametric studies can be carried out and a term-by-term analysis of the helicopter stability equations can be performed. This model has been validated with HOST and the triggering mechanism has been detailed. Finally, the influence of rotor, structure, and flight parameters has been evaluated and architectural considerations to avoid the appearance of such couplings are presented.

Ces dernières décennies de nombreux modèles de paliers à feuilles ont été développés. Aujourd'hui, la limite de ces modèles est apparente notamment au niveau de la compréhension des comportements non linéaire du système rotor palier et de la quantification de sa dissipation énergétique. Il est essentiel pour les développements futurs de maîtriser les instabilités liées au fonctionnement de ces paliers. Grâce à une approche variationnelle et la MEF, la structure flexible a été modélisée comme une structure mince soumise à la pression d'un fluide compressible, isotherme, laminaire puis turbulent. Nous tenons compte dans cette étude, des frottements secs internes en utilisant la loi de Coulomb et la méthode du Lagrangien augmenté. Le modèle de structure est couplé avec équations de Reynolds des films minces afin de déterminer le comportement du rotor à l'aide du principe fondamental de la dynamique. Nous avons montré la pertinence de l'approche choisie, notamment l'utilisation du modèle de structure mince sur le comportement dynamique du rotor et sur le champ de pression hénéré dans le palier. On démontre aussi l'intéraction entre les déflections des bumps et le frottement sec. L'action du flambage est doublement accentué par le phénomène de frottement présent entre les feuilles, modifiant ainsi la dissipation d'énergie dans le palier. Le second objectif a été d'identifier l'origine des phénomènes subsynchrones afin de développer des nouveaux paliers en se dédouanant des instabilités qu'elles engendrent. / These last decades numerous model for airfoil bearings have been developed. But nowadays, these models are not sufficiently accurate for the rotor response prediction in the presence of non linearities. It is essential for the future developments to control the instabilities due to the non linear behavior in order to quantify the energy dissipation in the bearings. By means of a variational approach, the flexible structure is modeled as a thin media subjected to a compressible fluid pressure, isothermal and in a laminar then turbulent regime. The model is built up using FEM for the foils response. the internal dry friction is taken into account with Coulomb’s law and the updated Lagrangian method. The structure model is coupled with Reynolds equation to calculate the rotor motions, thanks to the basic principle of dynamics (B.P.D). This work is performed, first, to put in evidence the influence of thin structure approach on the rotor behavior and on the field pressure. The link between bumps deflections and dry friction is established. The structure buckling is twice increased by the phenomenon of friction between sheets and energy dissipation. The second objective is to identify the subsynchronous frequencies in order to establish the relevance of the new airfoil model for non linear and instabilities investigations.

Cette thèse traite de la dynamique non-linéaire multi-contact des ensembles rotor/stator et s’applique en particulier aux tur-bomoteurs d’hélicoptère conçus par Turboméca, groupe Safran. L’amélioration des performances des turbines à gaz pousse les constructeurs à réduire les jeux fonctionnels rotor-stator no-tamment, tout en garantissant robustesse et fiabilité. Cela nécessite de développer des modèles les plus précis possible afin de prévoir et maîtriser des situations à risques telles que les interactions rotor/stator entre les parties fixes et tournantes déclen-chées principalement, dans le cas des turbomoteurs d’hélicoptère, par la perte d’aubes. La partie 1 présente une synthèse bibliographique des principaux phénomènes physiques rencontrés suite à une touche ro-tor/stator en s’appuyant sur l’expérimentation et le calcul. Un bilan sur les différents modèles numériques de gestion du con-tact frottant est détaillé. La dualité entre méthodes temporelles et fréquentielles est aussi abordée comme la méthode de la ba-lance harmonique et les schémas d’intégration temporelle de la famille de Newmark. Il est aussi décrit deux outils d’analyse fréquentielle : le spectrogramme pour analyser l’évolution d’un spectre fréquentiel dans le temps, le full-spectrum pour pren-dre en compte les précessions du rotor. La partie 2 se focalise sur des systèmes dynamiques académiques : un oscillateur forcé à double butées, un rotor de Jeffcott et un rotor à 3 disques avec tous deux une interaction disque/carter. Compte tenu du caractère transitoire du comportement des turbomoteurs, il s’agit de tester des méthodes d’intégration temporelle pas à pas et aussi des lois de contact. Il en ressort que la méthode de Newmark à accélération moyenne, et les lois de contact type « pénalité amortie » combinées à une régularisation de la raideur et de l’amortissement par une fonction arc tangente sont pertinentes. La modélisation de rotor en flexion en ré-gime transitoire et avec plusieurs touches possibles est réalisée avec la méthode des éléments finis et l’intégration des mé-thodes et techniques précédentes. L’ensemble de la modélisation est mise en œuvre sous l’environnement Matlab et se traduit au final par un logiciel nommé ToRoS (Touche Rotor-Stator). Le turbomoteur de l’Ardiden 1H fait l’objet de la dernière partie. Le logiciel ToRoS développé est utilisé pour prévoir la dyna-mique transitoire de sa turbine libre soumise à de multiples touches, consécutifs à un départ d’aubes. Les lois de contacts ap-pliquées dépendent du type de contact : disque/carter, labyrinthe/stator, palier/butée. Durant la descente en vitesse, la ligne d’arbre adopte, en fonction du niveau de balourd, de la vitesse de rotation, des paramètres du contact et du frottement, un comportement avec un contact quasi-permanent en précession directe. / This PhD thesis deals with the nonlinear transient dynamic response of rotor/stator assemblies in the case of multi-contacts, it is applied on Turbomeca’s helicopter turbo-engine. In order to improve gas turbine performances, constructors have to reduce rotor/stator clearances, while continuing to maintain component’s reliability, durability and safety. It implies the development of models to predict and control unsafe situations as, rotor/stator interactions between fixed and rotating parts, mainly triggered by a blade-loss in helicopters turbo-engine case. The first part of this document is concerned with a bibliographical summary of the main physical phenomena observed after a rotor/stator interaction, this is supported by experiments and numerical calculations. A review of the various sliding contact numerical models is presented. The duality between time and/or frequency simulation response methods as, harmonic balance method vs Newmark time integration scheme is discussed. Then two numerical tools for frequency domain analysis are described: the spectrogram to analyze frequency spectrum as a function of the time, the full-spectrum for analyzing the rotor whirl motions. The second part is focused on the time response simulation of some academic systems: an excited oscillator with two end-stops, a Jeffcott rotor and finally a 3 disks rotor both subjected to disk/casing interactions. Given the transient behavior exhibited by turbo-engine rotors following a rotor/stator contact, the purpose is to test several step-by-step time integration scheme combined with different contact laws. This analysis has shown that the Newmark scheme with constant acceleration used with damped contact penalty laws combined to stiffness and damping coefficients smoothed by arctangent functions are relevant. The rotor bending modeling during transient motion considering possible multi-contacts with the stator is realized using the finite element method and the previously reviewed contact modeling methods. The simulation is implemented under Matlab environment and is named ToRoS. (Rotor/Stator Touch). Finally, the developed modeling is applied to the Ardiden 1H turbo-engine. The ToRoS software is used to predict the transient dynamic response of the free power turbine subjected to multi-contacts, after a sudden blade-loss which is modeled by a sudden unbalance. Contact laws are applied and depend on contact type and location: disk/casing, seals, thrust bearing. Depending on the mass unbalance level, the speed of rotation, the contact and friction parameters, the rotor can be in a quasi-permanent contact state in forward whirl while the rotation speed is running-down

The aerodynamic integration of an aero-engine intake system with the airframe can pose some notable challenges. This is particularly so for many military air- craft and is likely to become a more pressing issue for both new military systems with highly embedded engines as well as for novel civil aircraft configurations. During the late 1960s with the advent of turbo-fan engines, industry became in- creasingly aware of issues which arise due to inlet total pressure distortion. Since then, inlet-engine compatibility assessments have become a key aspect of any new development. In addition to total temperature and total pressure distortions, flow angularity and the associated swirl distortion are also known to be of notable con- cern. The importance of developing a rigorous methodology to understand the effects of swirl distortion on turbo-machinery has also become one of the major concerns of current design programmes. The goal of this doctoral research was to further the current knowledge on swirl distortion, and its adverse effects on engine performance, focusing on the turbo-machinery components (i.e. fans or compressors). This was achieved by looking into appropriate swirl flow descriptors and by correlating them against the compressor performance parameters (e.g loss in stability pressure ratios). To that end, a number of high-fidelity three-dimensional Computational Fluid Dynamics (CFD) models have been developed using two sets of transonic rotors (i.e. NASA Rotor 67 and 37), and a stator (NASA Stator 67B). For the numerical purpose, a boundary condition methodology for the definition of swirl distortion patterns at the inlet has been developed. Various swirl distortion numerical parametric studies have been performed using the modelled rotor configurations. Two types of swirl distortion pattern were investigated in the research, i.e. the pure bulk swirl and the tightly-wound vortex. Numerical simulations suggested that the vortex core location, polarity, size and strength greatly affect the compressor performance. The bulk swirl simula- tions also showed the dependency on swirl strength and polarity. This empha- sized the importance of quantifying these swirl components in the flow distortion descriptors. For this, a methodology have been developed for the inlet-engine compatibility assessment using different types of flow descriptors. A number of correlations have been proposed for the two types of swirl distortion investigated in the study.

La fibrillation atriale (FA) est l’arythmie soutenue la plus fréquente ; elle entraine une majoration significative de la morbidité et de la mortalité. Les mécanismes qui en sont responsables sont encore incomplètement connus, et sa prise en charge n’est pas optimale. Afin de mieux comprendre la physiopathologie de la FA, nous avons mené différents travaux sur des coeurs de moutons isolés et perfusés par un système de Langendorff mais également en créant un modèle chronique de FA persistante de longue durée. Dans un modèle ovin de FA persistante, nous avons ainsi démontré que la fréquence dominante (DF) de la FA augmentait progressivement pendant les premières semaines de l’arythmie, alors que les épisodes étaient paroxystiques, phénomène en rapport avec le raccourcissement de la durée du potentiel d’action secondaire au remodelage électrophysiologique. La DF se stabilisait dès lors que la FA devenait persistante, une fois le remodelage électrophysiologique maximal. L’accélération de la DF (dDF/dt) était significativement corrélée au temps nécessaire à la transition vers la FA persistante. Le remodelage structurel n’apparaissait que secondairement, une fois l’arythmie devenue persistante. Sur le plan thérapeutique, nous avons étudié les mécanismes anti-arythmiques de la chloroquine (bloqueur d’IK1) et de la ranolazine (bloqueur d’INa), molécules entrainant un ralentissement de la fréquence de rotation des rotors, une diminution de la DF et un retour en rythme sinusal. Ces travaux nous ont permis de mieux appréhender le rôle des ces courants ioniques dans le maintien de la FA. Enfin, nous avons démontré l’efficacité de l’ablation de la FA en utilisant le cryoballon (CB) de deuxième génération, efficacité grevée d’un taux de parésie du nerf phrénique élevé, dont nous avons pu prédire la survenue à l’aide d’un prédicteur simple, la distance entre le bord du CB et la cathéter permettant de stimuler le nerf phrénique pendant l’application. Une meilleure compréhension des mécanismes à l’origine de l’initiation et du maintien de cette arythmie, ainsi qu’une meilleure prise en charge thérapeutique permettraient d’améliorer la qualité de vie des patients et d’en diminuer le taux de complications. / Atrial fibrillation (AF) is the most common sustained arrhythmia, significantly increasing patients’ morbidity and mortality. The mechanisms explaining the initiation and maintenance of the arrhythmia are incompletely understood, and the current treatment strategy is suboptimal. To better understand the pathophysiology of AF, we conducted various projects using Langendorff-perfused sheep hearts and a chronic model of long-standing persistent AF. In the model of persistent AF, we demonstrated that dominant frequency (DF) progressively increases during the first weeks of the arrhythmia, during its paroxysmal stage, due to the electrophysiological remodeling resulting in atrial action potential shortening. DF stabilizes once the electrophysiological remodeling is maximal, and the arrhythmia becomes persitent. The rate of DF increase (dDF/dt) was strongly correlated with the time to persistent AF. Structural remodeling appears secondarily, once transition has occured. We also studied the anti-arrhythmic mechanisms of chloroquine (IK1 blocker) and ranolazine (INa blocker), which slow the frequency of rotation of rotors, decrease the DF and favor reversal to sinus rhythm. These projects helped us to better understand the importance of these currents in AF dynamics. Lastly, we demonstrated the increased efficacy of AF ablation when using the second generation cryoballoon (CB), which regrettably increases the occurrence of phrenic nerve palsy. A simple, reliable predictor of this complication was found, the distance between the lateral edge of the CB and the phrenic nerve stimulating catheter. A better understanding of the mechanisms underlying the initiation and maintenance of AF, in conjunction with better therapeutic strategies will help to improve patients’ quality of life and decrease the complications of the arrhythmia.