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1
Narejo, Abdul Ahad. "3D design and simulations of NASA rotor 67." Thesis, University West, Department of Engineering Science, 2008. http://urn.kb.se/resolve?urn=urn:nbn:se:hv:diva-814.
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In this master\2019s thesis work, research has been carried out to develop an automated and parameterized programming model in Matlab to generate a standard journal file, which can read by Gambit and produce a meshed 2D and 3D blade. This file then can be exported into mesh-formatted file for fluent for further simulations and numerical results.
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Roca, León Enric. "Simulations aéro-mécaniques pour l'optimisation de rotors d'hélicoptère en vol d'avancement." Thesis, Nice, 2014. http://www.theses.fr/2014NICE4076.
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Un cadre d'optimisation multi-Objectif pour les pales d'hélicoptère est développé en utilisant des modèles de simulation de haute fidélité. Des fonctions objectives caractérisant la performance de l'hélicoptère en vol stationnaire et d'avancement sont retenues. Deux solveurs sont utilisés afin de prédire la performance du rotor: le code général HOST et le solveur CFD elsA. Le premier axe de recherche porte sur la caractérisation de la précision des méthodes de prédiction. L'influence de la prise en compte de la souplesse de la pale, du trim rotor et/ou de l'utilisation de modélisations aérodynamiques simplifiées est caractérisée pour chaque cas de vol en utilisant des mesures en soufflerie. Un cadre numérique adapté à l'optimisation est développé. Le deuxième axe de recherche porte sur des techniques d'optimisation multi-Objectif de pales en vol stationnaire et d'avancement. Deux algorithmes novateurs basés sur la compétition (Jeux de Nash) et la coopération (Descente à Gradients Multiples) sont présentés comme des alternatives aux approches traditionnelles pour traiter le problème multi-Objectif. Afin de réduire le coût des simulations, un cadre de simulation basé sur des métamodèles est développé y compris une stratégie multi-Fidélité pour prédire la performance du rotor en vol d'avancement. Ces techniques sont appliquées à un cas réaliste de rotor, en utilisant des simulations CFD trimmées avec pale souple pour le cas du vol d'avancement et des simulations CFD avec pale rigide en vol stationnaire. Les résultats sont ensuite analysés, démontrant le potentiel de ces techniques pour l'obtention de conceptions réalistes représentant des bons compromis entre les objectifsThis work addresses the development of a multi-Objective optimization framework for helicopter rotor blades using high-Fidelity simulation models. In particular, objective functions corresponding to hover and forward flight are considered. Two solvers are used to predict the rotor performance: the comprehensive rotor code HOST and the Computational Fluid Dynamics (CFD) solver elsA. The first research axis of this work is the characterization of the accuracy of each available prediction method. The influence of considering the blade elasticity, the rotor trim and/or simplified aerodynamics is characterized for each flight case using wind-Tunnel data. As a result, a numerical framework adapted to the optimization is developed. The second part of this work concerns the formulation and development of techniques adapted to the multi-Objective optimization of rotor blades in hover and in forward flight. Innovative algorithms based on competition (Nash Games) and cooperation (Multi-Gradient Descent) are presented as alternatives to traditional multi-Objective approaches. In order to reduce the simulation costs, a surrogate-Based framework is developed, including a multi-Fidelity strategy to predict the rotor performance in forward flight. These techniques are finally applied to a realistic rotor, considering trimmed elastic CFD computations in the forward flight case and rigid blade CFD computations in the hover case. The results are subsequently analyzed, demonstrating the potential of these techniques to obtain realistic designs realizing interesting trade-Offs
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Gupta, Vinit. "Quad tilt rotor simulations in helicopter mode using computational fluid dynamics." College Park, Md. : University of Maryland, 2005. http://hdl.handle.net/1903/3172.
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Thesis (Ph. D.) -- University of Maryland, College Park, 2005.Thesis research directed by: Aerospace Engineering. Title from t.p. of PDF. Includes bibliographical references. Published by UMI Dissertation Services, Ann Arbor, Mich. Also available in paper.
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Zhong, B. "Implicit multi-block Euler/Navier-Stokes simulations for hovering helicopter rotor." Thesis, Cranfield University, 2003. http://dspace.lib.cranfield.ac.uk/handle/1826/10754.
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A three dimensional
implicit multiblock Navier-Stokes solver for hovering rotor
vortical flow simulations has been developed. The governing equations used are
cast in an attached blade rotating frame. Two formulations of the governing
equations using the relative or absolute velocity as variables respectively are
employed and investigated. The Osher's approximate Riemann solver is used for
the convective fluxes evaluation. A modified MUSCL scheme is employed for
improving the accuracy of the discretisation for the in viscid fluxes. A Block
Incomplete Lower and Upper Decomposition (BILU) is adopted for solving the
linear
system resulted from the use of an implicit scheme. Special treatment for
the terms, including extra flux terms and source terms, arising from the non-
inertial reference
system are implemented. A multiblock technique is used to
obtain the
exibility for quality grid generation. The suitability of different grid
topologies for vortex wake capturing is demonstrated. Numerical tests show that
significant improvement in computational efficiency is achieved by utilising the
BILU
implicit scheme in both fixed wing and hovering rotor calculations.
Numerical simulations also demonstrate Navier-Stokes solutions give more
accurate results than that from Euler solutions, especially in transonic tip speed
cases.
Computed results including surface pressure distributions and tip vortex
trajectories are compared with the experimental data, which shows that the
developed solver and the numerical scheme can simulate hovering rotor flows
with
good accuracy.
5
Zhong, Bowen. "Implicit multi-block Euler/Navier-Stokes simulations for hovering helicopter rotor." Thesis, Cranfield University, 2003. http://dspace.lib.cranfield.ac.uk/handle/1826/10754.
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A three dimensional implicit multiblock Navier-Stokes solver for hovering rotor vortical flow simulations has been developed. The governing equations used are cast in an attached blade rotating frame. Two formulations of the governing equations using the relative or absolute velocity as variables respectively are employed and investigated. The Osher's approximate Riemann solver is used for the convective fluxes evaluation. A modified MUSCL scheme is employed for improving the accuracy of the discretisation for the in viscid fluxes. A Block Incomplete Lower and Upper Decomposition (BILU) is adopted for solving the linear system resulted from the use of an implicit scheme. Special treatment for the terms, including extra flux terms and source terms, arising from the non-inertial reference system are implemented. A multiblock technique is used to obtain the exibility for quality grid generation. The suitability of different grid topologies for vortex wake capturing is demonstrated. Numerical tests show that significant improvement in computational efficiency is achieved by utilising the BILU implicit scheme in both fixed wing and hovering rotor calculations. Numerical simulations also demonstrate Navier-Stokes solutions give more accurate results than that from Euler solutions, especially in transonic tip speed cases. Computed results including surface pressure distributions and tip vortex trajectories are compared with the experimental data, which shows that the developed solver and the numerical scheme can simulate hovering rotor flows with good accuracy.
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JACQUES, REMI. "Simulations numeriques d'ecoulements transitionnels et turbulents dans des configurations de type rotor-stator." Paris 11, 1997. http://www.theses.fr/1997PA112386.
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Ce travail de these porte sur l'etude numerique des ecoulements transitionnels et turbulents dans une cavite confinee formee de deux disques coaxiaux dont l'un est en rotation uniforme autour de son axe de revolution (rotor), et l'autre stationnaire (stator). Les simulations numeriques sont effectuees sous l'hypothese d'axisymetrie de l'ecoulement instantane. On utilise alors un code de calcul parallelise integrant une decomposition de domaine. Plusieurs caracteristiques des ecoulements entre deux disques tournants sont reproduites : existence de couches limites sur les deux disques tournants, separees par un region centrale de l'ecoulement en rotation moyenne uniforme, caractere plus instable de la couche limite liee au disque fixe. L'existence d'un regime d'ondes inertielles a egalement ete mis en evidence dans le cur de la cavite lorsque l'ecoulement est turbulent dans la couche limite liee au disque fixe. L'etude des equations de transport des tensions de reynolds montre que la rotation modifie les distributions spatiales de certains termes intervenant dans les bilans associes a ces equations. Ils mettent egalement en evidence les limitations de l'hypothese d'axisymetrie qui modifie alors des caracteristiques intrinseques de la turbulence. Des simulations numeriques tridimensionnelles avec un code de calcul parallelise sont alors effectuees pour le regime d'ecoulement laminaire instationnaire. Ces premieres simulations ont montre que l'hypothese d'axisymetrie stabilisait l'ecoulement. Enfin, les resultats de simulation numerique sont confrontes a des resultats fournis par une modelisation de la turbulence de type k - et des resultats experimentaux. Les deux methodologies numeriques fournissent des resultats relativement proches concernant les distributions de vitesse moyenne.
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Parthasarathy, Nikhil Kaushik. "An efficient algorithm for blade loss simulations applied to a high-order rotor dynamics problem." Thesis, Texas A&M University, 2003. http://hdl.handle.net/1969.1/189.
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In this thesis, a novel approach is presented for blade loss simulation of an aircraft gas turbine rotor mounted on rolling element bearings with squeeze film dampers, seal rub and enclosed in a flexible housing. The modal truncation augmentation (MTA) method provides an efficient tool for modeling this large order system with localized nonlinearities in the ball bearings. The gas turbine engine, which is composed of the power turbine and gas generator rotors, is modeled with 38 lumped masses. A nonlinear angular contact bearing model is employed, which has ball and race degrees of freedom and uses a modified Hertzian contact force between the races and balls and for the seal rub. This combines a dry contact force and viscous damping force. A flexible housing with seal rub is also included whose modal description is imported from ANSYS. Prediction of the maximum contact load and the corresponding stress on an elliptical contact area between the races and balls is made during the blade loss simulations. A finite-element based squeeze film damper (SFD), which determines the pressure profile of the oil film and calculates damper forces for any type of whirl orbit is utilized in the simulation. The new approach is shown to provide efficient and accurate predictions of whirl amplitudes, maximum contact load and stress in the bearings, transmissibility, thermal growths, maximum and minimum damper pressures and the amount of unbalanced force for incipient oil film cavitation. It requires about 4 times less computational time than the traditional approaches and has an error of less than 5 %.
8
Wells, Jesse Buchanan. "Effects of Turbulence Modeling on RANS Simulations of Tip Vortices." Thesis, Virginia Tech, 2009. http://hdl.handle.net/10919/34343.
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The primary purpose of this thesis is to quantify the effects of RANS turbulence modeling on the resolution of free shear vortical flows. The simulation of aerodynamic wing-tip vortices is used as a test bed. The primary configuration is flow over an isolated finite wing with aspect ratio, , and Reynolds number, . Tip-vortex velocity profiles, vortex core and wake turbulence levels, and Reynolds stresses are compared with wind tunnel measurements. Three turbulence models for RANS closure are tested: the Lumley, Reece, and Rodi full Reynolds stress transport model and the Sparlart-Allmaras model with and without a proposed modification. The main finding is that simulations with the full Reynolds stress transport model show remarkable mean flow agreement in the vortex and wake due to the proper prediction of a laminar vortex core. Simulations with the Spalart-Allmaras model did not indicate a laminar core and predicted over-diffusion of the tip-vortex.
Secondary investigations in this work include the study of wall boundary layer treatment and simulating the wake-age of an isolated rotorcraft in hover using a steady-state RANS solver. By comparing skin friction plots over the NACA 0012 airfoil, it is shown that wall functions are most effective in the trailing edge half of the airfoil, while high velocity gradient and curvature of the leading edge make them more vulnerable to discrepancies. The rotorcraft simulation uses the modified Spalart-Allmaras turbulence model and shows proper, qualitative, resolution of the interaction between the vortex sheet and the tip vortex.Master of Science
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Chatzisavvas, Ioannis [Verfasser], Bernhard [Akademischer Betreuer] Schweizer, and Wolfgang [Akademischer Betreuer] Seemann. "Efficient Thermohydrodynamic Radial and Thrust Bearing Modeling for Transient Rotor Simulations / Ioannis Chatzisavvas ; Bernhard Schweizer, Wolfgang Seemann." Darmstadt : Universitäts- und Landesbibliothek Darmstadt, 2018. http://d-nb.info/116838088X/34.
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Verley, Simon. "Evaluation du couple "champ lointain" d'un rotor d'hélicoptère en vol stationnaire : analyse de résultats issus de simulations numériques de mécanique des fluides." Phd thesis, Université d'Orléans, 2012. http://tel.archives-ouvertes.fr/tel-00904918.
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Dans cette thèse, une formulation pour l'extraction du couple " champ lointain " d'un rotor d'hélicoptère en vol stationnaire est présentée. Cette formulation est dérivée de la méthode d'extraction de la traînée " champ lointain " d'un avion, basée sur les travaux de van der Vooren et Destarac [?, ?, ?]. Un outil développé à l'Onera à partir de cette théorie permet de donner une analyse complète de la traînée aérodynamique d'un avion. Il est basé sur l'analyse physique et locale de l'écoulement calculé autour de l'aéronef, et décompose la traînée totale, aussi appelée traînée mécanique, en composantes physiques. Ces composantes physiques peuvent être définies comme suit : 1) la traînée d'onde, 2) la traînée visqueuse, 3) la traînée induite. L'adaptation de la méthode d'extraction de la traînée d'un avion à un rotor en vol stationnaire nécessite l'utilisation du couple rotor à la place de la traînée de l'avion, ce qui donne la décomposition suivante : 1) le couple d'onde, 2) le couple visqueux, 3) le couple induit. Les simulations de rotor diffèrent de celles de l'avion dans la mesure où les équations d'Euler (ou RANS) ne sont pas écrites dans le même repère de référence : les simulations d'avion utilisent généralement une formulation en vitesse relative tandis que les simulations d'un rotor d'hélicoptère utilisent la vitesse absolue projetée dans le repère relatif. Cette différence conduit à deux formulations différentes des équations de l'écoulement, et nécessairement deux formulations différentes de l'extraction de la traînée ou du couple. Ce changement de repère implique aussi des changements dans les quantités thermodynamiques utilisées, en particulier l'utilisation de la rothalpie à la place de l'enthalpie d'arrêt pour déterminer le couple dû aux phénomènes irréversibles. Une application de cette méthode est présentée sur un rotor quadripale créé pour cette étude et montre comment cette nouvelle approche peut améliorer la précision de l'extraction des performances d'un rotor à partir de résultat issu de la simulation numérique.
11
Hoinville, Eric. "Etude du sillage de rotors d'hélicoptère en configuration de Vortex Ring." Phd thesis, Orléans, 2007. http://www.theses.fr/2007ORLE2070.
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Les études sur le Vortex Ring State ont récemment reçu un regain d'intérêt suite à la mise en place de trajectoires d'approche à forte pente pour les atterrissages en ville qui conduisent à des conditions de vol proches des frontières du VRS. Dans les années antérieures, les aspects numériques ont été étudiés grâce à des méthodes empiriques ou des modèles analytiques, et des expériences ont été effectuées dans le but de mieux comprendre la physique du phénomène. Dans cette étude, le code CFD elsA a été utilisé dans le but de résoudre les équations d'Euler. Un balayage en vitesse de descente verticale avec différents maillages a été réalisé afin d'étudier la capacité du solveur à capturer le Vortex Ring State. Dans un premier temps, la précision de la représentation de l'écoulement a été évalué en fonction d'hypothèses numériques (stratégies et précision des maillages, consistance en temps des simulations,. . . ) et physiques (périodicité de l'écoulement, cinématique du rotor,. . . ). Ceci permet d'extraire les options pour effectuer, dans un second temps, des simulations les plus représentatives possible de l'état de VRS afin d'étudier et de pouvoir décrire les mécanismes d'apparition et d'évolution de ce phénomène.
12
D'Haudt, Emmanuel. "Étude expérimentale de l'influence des conditions périphériques sur un écoulement turbulent de type rotor-stator : premières confrontations avec des résultats de simulations numériques." Lille 1, 2006. https://pepite-depot.univ-lille.fr/LIBRE/Th_Num/2006/50376-2006-D_Haudt.pdf.
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Les recherches effectuées sur des écoulements turbulents dans des cavités interdisques ont permis de mettre en évidence l'importance des conditions aux limites. Ce présent travail a pour but de mieux comprendre les phénomènes qui régissent l'apparition de différents types d'écoulements observés dans une cavité rotor-stator non soumise à un flux radial forcé. Dans cette optique, un banc d'essais a été adapté pour étudier plus spécifiquement l'influence de deux paramètres géométriques, l'un lié à une faible différence entre le rayon des disques, l'autre relatif à la présence d'un carter permettant de supprimer l'écoulement produit par la paroi externe du rotor. La base de données constituée à partir de mesures effectuées principalement par anémométrie à fils chauds a été confrontée à des résultats de simulations numériques réalisés à l'aide du code de calcul FLUENT. L'analyse des résultats montre en particulier qu'à la périphérie du système, le fluide éjecté par l'effet centrifuge du rotor est nécessairement compensé par une injection provenant partiellement du fluide au repos situé à l'extérieur à la cavité, près du stator, et de la réintroduction du fluide éjecté par le rotor. La proportion entre ces deux sources, qui dépend étroitement des paramètres géométriques retenus, influe sur le niveau de pré-rotation du fluide en entrée de cavité et conditionne ainsi l'apparition des différents types d'écoulement observés, notamment l'écoulement en bloc de type Batchelor.
13
D'Haudt, Emmanuel Bois Gérard Debuchy Roger. "Étude expérimentale de l'influence des conditions périphériques sur un écoulement turbulent de type rotor-stator premières confrontations avec des résultats de simulations numériques /." Villeneuve d'Ascq : Université des sciences et technologies de Lille, 2007. https://iris.univ-lille1.fr/dspace/handle/1908/988.
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Reproduction de : Thèse de doctorat : Mécanique : Lille 1 : 2006.N° d'ordre (Lille 1) :3874. Résumé en français et en anglais. Titre provenant de la page de titre du document numérisé. Bibliogr. p. 171-173.
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Peres, Noele. "A 3D pseudospectral method for cylindrical coordinates. Application to the simulations of rotating cavity flows." Thesis, Aix-Marseille, 2012. http://www.theses.fr/2012AIXM4309/document.
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La simulation d'écoulements dans des cavités cylindriques en rotation présente une difficulté particulière en raison de l'apparition de singularités sur l'axe. Le présent travail propose une méthode collocative pseudospectrale suffisamment efficace et précise pour surmonter cette difficulté et résoudre les équations 3D de Navier-Stokes écrites en coordonnées cylindriques. Cette méthode a été développée dans le cadre des différentes études menées au laboratoire M2P2, utilisant une méthode collocative de type Chebychev dans les directions radiale et axiale et Fourier-Galerkin dans la direction azimutale [thêta]. Pour éviter de prescrire des conditions sur l'axe, une nouvelle approche a été développée. Le domaine de calcul est défini par (r,[thêta],z)∈[-1,1]×[0,2π]×[-1,1] avec un nombre N pair de points de collocation dans la direction radiale. Ainsi, r=0 n'est pas un point de collocation. La distribution de points de type Gauss-Lobatto selon r et z densifie le maillage seulement près des parois ce qui rend l'algorithme bien adapté pour simuler les écoulements dans des cavités cylindriques en rotation. Dans la direction azimutale, le chevauchement des points dû à la discrétisation est évitée par l'introduction d'un décalage égal à π/2K à [thêta]>π dans la transformée de Fourier. La méthode conserve la convergence spectrale. Des comparaisons avec des résultats expérimentaux et numériques de la littérature montrent un très bon accord pour des écoulements induits par la rotation d'un disque dans des cavités cylindriques ferméesWhen simulating flows in cylindrical rotating cavities, a difficulty arises from the singularities appearing on the axis. In the same time, the flow field itself does not have any singularity on the axis and this singularity is only apparent. The present work proposes an efficient and accurate collocation pseudospectral method for solving the 3D Navier-Stokes equations using cylindrical coordinates. This method has been developed in the framework of different studies of rotor-stator flows, using Chebyshev collocation in the radial and axial directions and Fourier-Galerkin approximation in the azimuthal periodic direction [thêta]. To avoid the difficulty on the axis without prescribing any pole and parity conditions usually required, a new approach has been developed. The calculation domain is defined as (r,[thêta];,z)∈[-1,1]×[0,2π]×[-1,1] using an even number N of collocation points in the radial direction. Thus, r=0 is not a collocation point. The method keeps the spectral convergence. The grid-point distribution densifies the mesh only near the boundaries that makes the algorithm well-suited to simulate rotating cavity flows where thin layers develop along the walls. In the azimuthal direction, the overlap in the discretization is avoided by introducing a shift equal to π/2K for [thêta]>π in the Fourier transform. Comparisons with reliable experimental and numerical results of the literature show good quantitative agreements for flows driven by rotating discs in cylindrical cavities. Associated to a Spectral Vanishing Viscosity, the method provides very promising LES results of turbulent cavity flows with or without heat transfer
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Dyachuk, Eduard. "Aerodynamics of Vertical Axis Wind Turbines : Development of Simulation Tools and Experiments." Doctoral thesis, Uppsala universitet, Elektricitetslära, 2015. http://urn.kb.se/resolve?urn=urn:nbn:se:uu:diva-260573.
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This thesis combines measurements with the development of simulation tools for vertical axis wind turbines (VAWT). Numerical models of aerodynamic blade forces are developed and validated against experiments. The studies were made on VAWTs which were operated at open sites. Significant progress within the modeling of aerodynamics of VAWTs has been achieved by the development of new simulation tools and by conducting experimental studies. An existing dynamic stall model was investigated and further modified for the conditions of the VAWT operation. This model was coupled with a streamtube model and assessed against blade force measurements from a VAWT with curved blades, operated by Sandia National Laboratories. The comparison has shown that the accuracy of the streamtube model has been improved compared to its previous versions. The dynamic stall model was further modified by coupling it with a free vortex model. The new model has become less dependent on empirical constants and has shown an improved accuracy. Unique blade force measurements on a 12 kW VAWT were conducted. The turbine was operated north of Uppsala. Load cells were used to measure the forces on the turbine. A comprehensive analysis of the measurement accuracy has been performed and the major error sources have been identified. The measured aerodynamic normal force has been presented and analyzed for a wide range of operational conditions including dynamic stall, nominal operation and the region of high flow expansion. The improved vortex model has been validated against the data from the new measurements. The model agrees quite well with the experiments for the regions of nominal operation and high flow expansion. Although it does not reproduce all measurements in great detail, it is suggested that the presented vortex model can be used for preliminary estimations of blade forces due to its high computational speed and reasonable accuracy.
16
Sauvage, Bastien. "Approximation et adaptation numériques pour les écoulements en machines tournantes." Electronic Thesis or Diss., Université Côte d'Azur, 2024. http://www.theses.fr/2024COAZ5045.
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Ce travail s'inscrit dans un projet de recherche dont l'objectif est de proposer des simulations numériques en fluides (CFD) capables de capturer le bruit produit par les machines tournantes.Cette thèse, au sein de ce projet, à pour objectif d'étudier des méthodes d'adaptation de maillages (instationnaires) pour des écoulements turbulents instationnaires.On commence par décrire les outils nécessaires à nos études, à savoir les méthodes numériques, les modèles de turbulences et l'adaptation de maillages. Une première partie est consacrée à l'étude de l'algorithme d'adaptation de maillage instationnaire "Transient Fixed Point" appliqué à des écoulements turbulents autour de cylindres à différents nombre de Reynolds. Puis on étudie une méthode pour prendre en compte la rotation dans les simulations,que l'on couple avec les méthodes d'adaptation de maillage. Des exemples numériques sont proposés.Ces premiers travaux se heurtent à deux importants problèmes ouverts en CFD maillage-adaptative.Afin de choisir de manière optimale le pas d'avancement en temps implicite, on présente une nouvelle méthode d'adaptation de maillages espace-temps, qui permet d'adapter simultanément le maillage en espace et le maillage en temps. Afin d'adapter le maillage à la fois à l’écoulement moyen et aux grandes structures turbulentes, on propose une nouvelle approche d'adaptation de maillage pour la turbulence en calcul LES et hybrideThis work is part of a research project aimed at proposing numerical fluid simulations (CFD) capable of capturing the noise produced by rotating machines.The aim of this thesis is to study mesh adaptation methods for unsteady turbulent flows. We begin by describing the tools required for our studies, namely numerical methods, turbulence models and mesh adaptation. The first part is devoted to the study of the "Transient" unsteady mesh adaptation algorithms applied to turbulent flows around cylinders at different Reynolds numbers. A method for taking rotation into account in simulations is then studied, and coupled with mesh the adaptation methods. Numerical examples are proposed.This initial work encounted two major unsolved problems in CFD mesh-adaptation. In order to optimally select the implicit time step, a new space-time mesh adaptation method is presented, which simultaneously adapts the space mesh and the time mesh. In order to adapt the mesh to both mean flow and large turbulent structures, a new mesh adaptation approach is proposed for turbulence in LES and hybrid computation
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Oliveira, Cássia Pederiva de. "Análise do desempenho de uma turbina savonius helicoidal com torção de 180º empregando simulação numérica." reponame:Biblioteca Digital de Teses e Dissertações da UFRGS, 2014. http://hdl.handle.net/10183/108528.
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Este trabalho apresenta a simulação numérica do escoamento turbulento em torno de uma turbina eólica de eixo vertical de pequeno porte, Savonius tipo helicoidal com torção de 180° nas pás. Com o intuito de avaliar a metodologia computacional empregada os resultados numéricos obtidos são comparados com os resultados experimental e numérico contidos no estado da arte. Também, compara-se o coeficiente de toque da turbina Savonius helicoidal com a turbina Savonius convencional. As simulações numéricas são baseadas no Método de Volumes Finitos, e para tal emprega-se o programa Fluent /Ansys versão 13.0 que resolve as equações da continuidade e as equações de Navier-Stokes com médias de Reynolds, juntamente com o modelo de turbulência . As simulações são desenvolvidas empregando diferentes malhas computacionais em estudos transientes, tridimensionais, com a turbina estacionária. A avaliação da qualidade da malha é realizada através do método de Índice de Convergência de Malha (GCI) o qual analisa o quão longe os resultados estão da solução assintótica para a malha utilizada. Após a análise da qualidade de malha, realizam-se simulações com a turbina em rotação as quais fazem uso da malha contendo uma região móvel possibilitando a imposição de uma velocidade angular ao rotor. O coeficiente de torque é obtido nas simulações e a partir dele calcula-se o coeficiente de potência. Além da análise do desempenho do rotor realiza-se uma análise qualitativa das características do escoamento sobre a turbina. A turbina Savonius helicoidal apresenta um valor de coeficiente de potência de 0,175 para a razão de velocidade de ponta de 0,58 considerando correção do efeito de bloqueio. Os resultados obtidos apresentam boa concordância com os resultados publicados por outros autores.This dissertation presents the numerical simulation of the turbulent flow around of a small sized vertical axis wind turbine, consisting in a helical Savonius type with a 180° degree of blade twist. In order to evaluate the used methodology the obtained results are compared with the state of the art numerical and experimental data. It will be also presented the comparison between the torque coefficient of the conventional Savonius turbine and the helical Savonius turbine. The numerical simulations are based on the Finite Volume Method (FVM), using the commercial code Fluent/ANSYS version 13.0, which solves the continuity and Navier-Stokes through the Reynolds time-averaged methodology, including the turbulence model. The simulations are developed using different computational meshes for transient and three-dimensional studies with the stationary turbine. The evaluating the quality of the mesh is performed by of Grid Convergence Index (GCI) method which analyzes how far the results are the asymptotic solution to the mesh used. After the evaluation of the mesh quality, it was simulated a case considering the rotor motion using the moving mesh configuration, allowing the imposition of an angular velocity to the turbine. In the post-processing stage, it is possible to obtain the torque coefficient on the rotor shaft, allowing the calculation of the power coefficient for the turbine. In addition to the performance analysis, it is also made a qualitative analysis of the flow characteristics over the turbine rotor and in both cases presenting a good correspondence with the results in the literature. The helical Savonius turbine presents a value of power coefficient of 0.175 to a tip speed ratio of 0.58 whereas blocking effect correction.
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Das, Suma Rani. "Investigation of Design and Operating Parameters in Partially-Filled Rubber Mixing Simulations." University of Akron / OhioLINK, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=akron1479151141596147.
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Ali, Mohamed. "Caractérisation et instabilités des tourbillons hélicoïdaux dans les sillages des rotors." Thesis, Aix-Marseille, 2014. http://www.theses.fr/2014AIXM4708/document.
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Les tourbillons hélicoïdaux générés derrière les rotors sont étudiés. Pour les générer, une méthode basée sur le couplage entre la technique de la ligne active et un solveur des équations de Navier-Stokes (ENS), incompressibles et tridimensionnelles, a été développée. Elle consiste à modéliser la pâle par son équivalent de forces volumiques. Les équations, écrites en coordonnées cylindriques, sont résolues par un schéma de différences finies, écrit en parallèle. La méthode est d'ordre deux en temps et en espace. Le solveur des ENS a été validé par la reproduction des taux de croissance d'un écoulement de jet, instable, trouvés par la théorie d'instabilité linéaire. La comparaison avec des données expérimentales a montré que la méthode prédit bien l'aérodynamique de la pâle. Ensuite, le tourbillon de bout de pâle a été, en particulier, caractérisé. La vorticité et la vitesse azimutale ont été trouvées auto-similaire et la taille du coeur suit asymptotiquement la loi de diffusion linéaire 2D. Un modèle simple du coeur du tourbillon a été proposé. La présence d'une vitesse axiale dans le coeur du tourbillon a été montrée et a été caractérisée en fonction du rapport de vitesse au bout de la pâle. Finalement, une étude de stabilité du tourbillon a été faite en utilisant une vitesse angulaire variable pour perturber l'écoulement. Les taux de croissances des modes les plus instables sont en bon accord avec celui de l'instabilité d'appariement 2D des tourbillons. Trois types de modes ont été identifiés en fonction de la fréquence des perturbations et ont été trouvés similaires aux modes décrits par la théorie et aussi trouvés, précédemment, par l'expérienceThis present work is aimed to study helical vortices encountered in the wakes of rotating elements. For this, the generation of a helical wake of a one-bladed-rotor in a laminar velocity field, is simulated by the actuator line method. This method is a coupling of a Navier-Stokes (NS) solver with the Actuator Line Method where the blade is replaced by the body forces. This method has been implemented in a finite difference code, that we have written in parallel to solve the 3D incompressible NS equations written in cylindrical coordinates. The order of accuracy of the method is two both in time and space. The NS solver was validated comparing growth rates of an unstable jet, found numerically, and those of linear instability theory. A good agreement was found. A good agreement was also found comparing numerical results to analytical formulations and experimental data. It was shown that the method predicts well the blade aerodynamics . Then, the helical tip vortex is characterized for different Reynolds numbers and Tip Speed Ratios. The vorticity and the azimuthal velocity were found self-similar and the vortex core follows asymptotically the linear 2D diffusion law. A simple model for the helical vortex core was proposed. The presence of an axial velocity inside the vortex core was highlighted. Then, a stability study of the helical tip vortex was done using an angular velocity dependent on time to perturb the flow. The largest growth rates were found in good agreement with those of the (2D) pairing instability. Three types of modes were identified based on the perturbation frequency. The results are similar to those found in previous analytical and experimental works
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Velkova, Cvetelina Vladimirova. "Modélisation du comportement dynamique des rotors d’hélicoptères." Thesis, Paris, ENSAM, 2013. http://www.theses.fr/2013ENAM0055/document.
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Modélisation du comportement dynamique des rotors d'hélicoptèresL'objectif de la thèse est l'étude et la modélisation du comportement dynamique et aérodynamique du rotor de l'hélicoptère en considérant à la fois les forces d'inertie et les forces aérodynamiques et en tenant compte des déformations élastiques des pales. L'algorithme de couplage proposé permet d'effectuer le calcul transitoire avec échange de données entre les solveurs fluide et structure à chaque pas de temps.La particularité de cette étude est l'utilisation du modèle aérodynamique de la ligne active, qui représente les forces de pale appliquées au fluide par des termes sources. Ces termes sources sont répartis dans les cellules de maillage à l'emplacement de la pale. Ainsi, la rotation, la torsion et le battement de la pale peuvent être représentés sans aucune déformation du maillage. Un avantage de la ligne active est que la simulation utilise un nombre réduit de nœuds, car des conditions aux limites «lois des parois» ne doivent pas être modélisées.Le cas d'un petit rotor expérimental d'hélicoptère est étudié en vol d'avancement. Les solveurs de fluide et de structure sont couplés pour calculer le comportement aérodynamique et dynamique du rotor. Pour ce faire, un algorithme de couplage faible en série décalé est appliqué. Les calculs itératifs sont contrôlés par un code spécialement conçu. Au début de chaque itération, le code calcule et répartit les termes sources dans le domaine fluide. A la fin du pas de temps, le code exécute le solveur de calcul de structure pour calculer un seul pas de temps. Ce solveur calcule le déplacement de la pale sous l'effet des forces aérodynamiques, élastiques et d'inertie et renvoi les résultats au solveur fluide. Les déplacements de la pale calculés servent de référence pour le solveur fluide au pas de temps suivant, pour distribuer les termes sources. Le calcul s'arrête lorsque le critère de convergence est vérifié.Afin de valider le cas simulé, des expérimentations sont réalisées en soufflerie. La puissance et la poussée aérodynamique du rotor sont mesurées. La Vélocimétrie par images de particules (PIV) est utilisée pour obtenir le champ de vitesse autour du rotor. Les mesures PIV à phase bloqué dans des plans azimutaux ont permis de reconstituer le champ d'écoulement 3D. La comparaison entre les résultats numériques et les expériences montre un bon accord et permet de valider la méthode de couplage proposéeMODELING THE DYNAMIC BEHAVIOR OF HELICOPTER ROTORThe aim of the thesis is the investigation and modeling of dynamic and aerodynamic behavior of helicopter rotor considering both inertial and aerodynamic forces and taking into account the elastic deformation of the blades. The proposed coupling algorithm allows the transient calculations with data exchange between the fluid and structure solvers at each time step.The particularity of this research is the use of an actuator line aerodynamic model, which represents the blade forces applied to the fluid as source terms. These source terms are distributed in the grid cells where the blade is located. Thus the rotation, flapping and torsion of the blade can be represented without any grid deformation. An advantage of the actuator line is that the simulation uses a reduced number of nodes, because the “wall” boundary conditions do not need to be modeled.The case of small experimental helicopter rotor is studied in forward flight. The fluid and structure solvers are coupled to calculate aerodynamic and dynamic behavior of the rotor. For this purpose, a loosely coupling serial staggered algorithm is applied. The iterative calculations are controlled by specially developed code. At the beginning of each iteration, this code calculates and distributes the source terms in the fluid domain. At the end of the time step, the code runs the structural solver to execute a single time step. This solver calculates the blade displacement under aerodynamic, elastic and inertial forces, and the results are returned to the fluid solver. The calculated blade displacements serve as reference in the next fluid step to distribute the source terms. The calculation stops when the convergence criteria are met.In order to validate the simulated case, measurements are carried on in the wind tunnel. The power and aerodynamic thrust of the rotor are measured. Particle Image Velocimetry (PIV) is used to obtain the velocity field around the rotor. Phase locked measurement in azimuth planes enabled to reconstruct 3D flow field. The comparison between numerical results and experiments shows good agreement and permits to validate the proposed coupling method
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ANNA, RICARDO E. SILVA DE SANT. "ROTOR ACCIDENT ANALYSIS: MODELLING AND SIMULATION." PONTIFÍCIA UNIVERSIDADE CATÓLICA DO RIO DE JANEIRO, 2007. http://www.maxwell.vrac.puc-rio.br/Busca_etds.php?strSecao=resultado&nrSeq=11885@1.
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A Dissertação aqui apresentada descreve um acidente em um
rotor de máquina de grande porte (compressor de ar) de uma
fábrica de fertilizante cujas conseqüências foram perdas
financeiras de alta monta tanto para a empresa quanto para o
Estado, pela importância econômica onde a fábrica
é situada. O objetivo da Dissertação foi simular
matematicamente o acidente ocorrido e esclarecer o mesmo.
Para se chegar ao diagnóstico do problema se modelou o rotor
e o discretizou pelo Método de Elementos Finitos. As
técnicas de investigação do problema e a sua seqüência de
investigação podem ser tomadas como base em investigação de
eventuais acidentes envolvendo rotores futuramente. O
capítulo relativo a Análise Modal será extraído como base de
apostila para curso envolvendo pessoal da área de
Manutenção Mecânica.A problem related with an air compressor gave birth to the MSc Thesis. Problems related with rotative machines are usual in the industrial field. Difficulties come from the data gathering in order to analyze, and propose a theory of failure in order to explain and avoid the recurrence of such problem. Modelling a rotor with a Timoshenko beam element and the discretization by finite element method permit the dynamical analysis and the modal analysis of the rotor considering its interaction with the radial and thrust bearings (assuming stiffness and rigidity). The work is divided in seven chapters: chapter one introduces the work and gives the overview of it; chapter two describes the industrial problem; chapter three is a brief explanation of bearing types and the fundamental principle of lubrication; chapter four introduces vibration theory and modal analysis; chapter five introduces the finite element method; chapter six is the simulation of the problem, using tailor-made MATLABr programs to reconstruct the problem and to compare the test field results with the here mentioned formulation; chapter seven discusses the results and proposes future works. Appendix shows the kinetic theory and the beam deformation model used in the program and the Laval simple rotor as a limited description of the dynamic of a rotor with distributed mass, rigidity and stiffness. The aim of this work is to help understand and avoid the recurrence of the failure described and to easy the understanding of modal analysis for new engineers and technicians which will deal with rotor dynamics.
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Collins, Kyle Brian. "A multi-fidelity framework for physics based rotor blade simulation and optimization." Diss., Atlanta, Ga. : Georgia Institute of Technology, 2008. http://hdl.handle.net/1853/26481.
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Thesis (Ph.D)--Aerospace Engineering, Georgia Institute of Technology, 2009.Committee Co-Chair: Dr. Dimitri Mavris; Committee Co-Chair: Dr. Lakshmi N. Sankar; Committee Member: Dr. Daniel P. Schrage; Committee Member: Dr. Kenneth S. Brentner; Committee Member: Dr. Mark Costello. Part of the SMARTech Electronic Thesis and Dissertation Collection.
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Sparv, Lisa. "Cooling simulation of a BEV electrical machine rotor." Thesis, KTH, Fordonsdynamik, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-302143.
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The thesis work described in this report is about simulation of the cooling of an electrical machine rotor. Limitations and simplifications were made on the CAD model of the rotor with the purpose of reducing the simulation time, for it to then be used for CFD-simulations using STAR-CCM+. This was done to see the temperature, as well as its distribution, in the model. By changing various parameters, one at the time whilst the rest were kept at their assigned standard values, the changes could be analysed and thereafter compared. The tests include smaller geometry changes, parameters of the coolant and its flow, parameters for the airgap and the materials in the laminates and the material around the magnets, as well as changes in loss values. The simulations for geometry changes involving the magnets and their surrounding material resulted in minor temperature increases. An inner rotor radius increase gave a relatively large temperature decrease (although this change would be more difficult to make in practice). Most of the mean values of the temperature changes in the regions of the model were within 10% from the standard simulation used. Increased thermal contact resistance between the Bakelite and the laminates, and increased losses had the worst impact on the cooling. Meanwhile the changes in coolant parameters (as well as the its inlet temperature and mass flow) and reduced losses had the best impact on the cooling. Generally, the temperature distributions looked similar for the different simulations. There were more differences in the distributions for the simulations with changed material properties or thermal contact resistance.Examensarbetet som beskrivs i denna rapport handlar om simulering av kylningen av en elmaskinsrotor. Avgränsningar och vissa förenklingar gjordes på en CAD modell av rotorn för att reducera simuleringstiden. Sedan användes CFD-simuleringsprogrammet STAR-CCM+ för att simulera temperaturfördelningen i modellen. Genom att ändra olika parametrar, en åt gången medan resten hölls vid sina bestämda standardvärden, kunde förändringarna undersökas och sedan jämföras. Det som testades inkluderar bland annat mindre geometriförändringar, parametrar för kyloljan och dess flöde, parametrar för luftgapet och materialen i laminaten och runt permanentmagneterna, samt förlustförändringar. Geometriförändringarna som gjordes för magneterna och det omgivande materialet gav små temperaturökningar. En ökad inre radie på rotorn gav relativt stor temperaturminskning (men denna ändring vore svårare att genomföra på rotorn i praktiken). Majoriteten av medelvärdena av modellregionernas temperaturförändringar var inom 10% från standardsimuleringen som användes. Ökat termiskt kontaktmotstånd mellan Bakeliten och laminaten samt ökade förluster hade sämst påverkan för kylningen, medan förändring i kylvätskans egenskaperna (samt inflödestemperaturen och massflödet) samt minskade förluster hade bäst inverkan. Generellt så såg temperaturfördelningarna lika ut för de olika simuleringarna. Det var främst när materialegenskaperna eller det termiska kontaktmotståndet ändrades som fördelningen såg annorlunda ut.
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Lindemann, Sylvester. "Model updating an einem biegeelastischen Rotor." Kassel Kassel Univ. Press, 2008. http://d-nb.info/994322720/04.
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McVicar, J. Scott G. "A generic tilt-rotor simulation model with parallel implementation." Thesis, University of Glasgow, 1993. http://theses.gla.ac.uk/4952/.
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The unique capabilities of the tilt-rotor configuration are generally accepted to provide significant potential when applied to numerous civil and military operations. A vital stage in the development of any tilt-rotor design is the simulation of its basic flying qualities which are essentially defined by the vehicle's response to a range of control inputs and the trim states it adopts. In order to carry out this simulation satisfactorily, an accurate generic mathematical model is required, however, the author is unaware of any existing tilt-rotor simulations which utilise the latest modelling techniques. A generic tilt-rotor simulation model (GTILT) which includes individual blade modelling to describe the behaviour of the rotor has been developed during this research. One of the most significant attributes of individual blade models is that they portray the oscillatory nature of the forces and moments produced by a lifting rotor. The resulting trimmed flight path of the vehicle is periodic rather than steady in nature and consequently existing trimming algorithms, formulated for use with rotor disc representations, are inappropriate when applied to individual blade simulations. A specialised trimming algorithm capable of rapidly trimming rotorcraft simulations to a specified periodic trim state has been developed and incorporated into the GTILT model. Individual blade modelling provides a higher level of fidelity than is possible when using a rotor disc representation but this benefit is obtained at the expense of computational burden. Hence, most sequential computing facilities are unable to provide the performance necessary to make such models practical. In order to reduce computational run-times to an acceptable level GTILT has been parallelised and implemented on a custom designed transputer network. GTILT has been configured using XV-IS data in order to investigate the fidelity of its predicted trim states and vehicle response to a range of control inputs. During the course of this investigation, the trim algorithm is shown to be robust and capable of producing rapid convergence to a wide range of trim states. Longitudinal trims predicted by GTILT are verified against those of the similarly configured Bell C81 for a range of nacelle incidences and good correlation obtained in all cases. A qualitative verification of the trim states adopted in turning flight reveals no anomalies and the results obtained are very encouraging. The dynamic response of the vehicle is demonstrated to be qualitatively valid when a range of control inputs are applied at various nacelle incidences with the behaviour of the vehicle being explicable in all cases.
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Hanotel, Roland. "Simulation expérimentale et numérique de l'intéraction rotor-fuselage d'hélicoptère." Aix-Marseille 2, 1991. http://www.theses.fr/1991AIX22075.
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L'etude de l'interaction rotor fuselage d'helicoptere et de la modelisation de ces effets d'interaction est cruciale pour l'amelioration des qualites de vol des helicopteres. Un code de calcul d'interaction aerodynamique rotor fuselage a ete developpe. Il se fonde sur la theorie de la ligne portante pour la representation des pales ; le sillage du rotor est discretise sous la forme de lanieres tangentielles et radiales. Le fuselage est represente par une repartition surfacique de sources et de doublets. Le calcul d'interaction s'appuie sur un processus iteratif entre l'influence du rotor et celle du fuselage. Des calculs rotor isole et des calculs couples rotor fuselage ont ete effectues pour analyser l'influence du fuselage. La validation de ce code a ete realisee sur les vitesses induites a l'aide de deux banques de donnees
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Jung, Alexander. "Berechnung der Stator-Rotor-Wechselwirkung in Turbomaschinen." [S.l. : s.n.], 2000. http://www.bsz-bw.de/cgi-bin/xvms.cgi?SWB8862171.
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Yucekayali, Arda. "Development Of A Comprehensive And Modular Modelling, Analysis And Simulation Tool For Helicopters." Master's thesis, METU, 2011. http://etd.lib.metu.edu.tr/upload/12613643/index.pdf.
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Helicopter flight dynamic, rotor aerodynamic and dynamic analyses activities
have been a great dispute since the first helicopters, at both design and test stages.
Predicting rotor aerodynamic and dynamic characteristics, helicopter dynamic
behavior and trimmed flight conditions is a huge challenge to engineers as it
involves the tradeoff between accuracy, fidelity, complexity and computational cost.
Flight dynamic activities such aspredicting trim conditions, helicopter dynamic behavior and simulation of a flight condition or maneuver mostly require analysis tools with low computational cost and complexity. However this decreases accuracy and fidelity of the model. On the other hand, analyses at design stages, such as
blade geometric and structural design mostly requires accurate and higher fidelity aerodynamic load predictions over the rotor disk. Contrarily this brings high computational cost and complexity. Therefore separate analysis tools for each objective or one complete tool that can be used for all purposes are essential. Throughout this study a helicopter mathematical including trim model with a selective and modular structure is developed as a generic analysis tool. The selective structure enables the mathematical model to be used in both flight dynamic and comprehensive analysis while the modular structure plays a role as an infrastructure for further developments. The mathematical model developed is validated with flight test data of several helicopters. Besides, commercial helicopter comprehensive analysis tools are used to validate the mathematical model analyses. Results showed good agreement with the compared data.
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Lipian, Michal. "Modèle hybride pour simuler l’écoulement à travers un birotor éolien caréné et sa validation expérimentale." Thesis, Paris, ENSAM, 2018. http://www.theses.fr/2018ENAM0073/document.
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La thèse résume la recherche sur le fonctionnement et l’écoulement autour d’une éolienne caréné à deux rotors. Le placement d’une turbine à l’entrée d’un canal divergent permet d’augmenter le débit massique à travers le rotor. Afin de mieux tirer parti de l’augmentation de la vitesse du vent à l’entrée du diffuseur, il a été décidé d’examiner la possibilité de placer un deuxième rotor, tournant dans le sens opposé, dans cette zone.L'étude menée combinait plusieurs voies de recherche différentes, y compris les méthodes de la mécanique des fluides numérique (CFD) et des études expérimentales. Cela a permis de mieux comprendre la nature de l'écoulement et du fonctionnement d'une éolienne à deux rotors. Des recherches expérimentales ont été menées dans la soufflerie de l’Institut de Turbomachinerie de l’Ecole Polytechnique de Lodz (Pologne). Une série de mesures de systèmes d'éoliennes divers, avec et sans carénage, à un et deux rotors, a été réalisée. Les résultats recueillis ont permis de confirmer que le carénage pouvait augmenter considérablement (même deux fois) l'efficacité du rotor. Cependant, les forces aérodynamiques et la vitesse de rotation augmentent également. Cet inconvénient peut être partiellement résolu en utilisant un deuxième rotor et en répartissant les charges aérodynamiques sur deux étages de turbine.Une partie importante de l'étude était les simulations numériques. Ils ont permis de préciser la nature et les paramètres de l'écoulement et d'estimer leur impact sur les performances de l'éolienne. Deux modèles numériques différents ont été développés:• Modèle rotor complet (anglais : Fully-resolved Rotor Model, FRM): modèle URANS dans ANSYS CFX, basé sur la discrétisation de la géométrie complète du rotor; ce modèle a été utilisé pour l'analyse de l’écoulement,• Modèle hybride CFD-BET (théorie de l’élément de pâle): modèle RANS dans ANSYS Fluent, dans lequel le rotor est représenté par les termes source dans les équations de Navier-Stokes, déterminés par un code interne; ce modèle a été utilisé pour évaluer les performances de différentes configurations d'éoliennes.Au cours de la recherche, une correction empirique interne de la perte d’extrémité de la pâle (anglais : tip loss correction) a été proposée, en tenant compte de l’influence du diffuseur. L’étude réalisée a permis d’observer, entre autres, que le déplacement du rotor en aval vers la sortie du diffuseur pouvait entraîner une réduction de la vitesse du vent à travers le rotor en amont, placé à l’entrée du diffuseur, et une diminution de la puissance globale du systèmeDoctoral dissertation summarizes the research on the functioning and flow around a two-stage, shrouded wind turbine. Placing the turbine at the inlet of a diverging channel allows to increase the mass flow rate of the flow through the rotor. To better take advantage of the increase in wind speed at the diffuser inlet, it was decided to examine the possibility of placing a second rotor in this area, with the opposite direction of rotation.The conducted study combined several different research paths, including Computational Fluid Dynamics (CFD) methods and experimental studies. This allowed for a more refined understanding of the nature of the flow and operation of a wind turbine with two rotors. Experimental research was carried out in the IMP TUL wind tunnel. A series of measurements of various turbine systems with and without shroud, with single- and double-rotor wind turbine were made. The collected results allowed to confirm that the shrouding can significantly (even twice) increase the efficiency of the rotor. However, aerodynamic forces and rotational speed also increase. This disadvantage can be partially addressed by using a second rotor and distributing aerodynamic loads to two turbine stages.An important part of the study were numerical simulations. They allowed to specify in more detail the nature and parameters of the flow and to estimate their impact on the performance of the wind turbine. Two different numerical models were developed:• Fully-resolved Rotor Model: URANS model in ANSYS CFX, based on discretising the entire geometry of the rotor, used for the flow analysis,• Hybrid model CFD-BET (Blade-Element Theory): RANS model in ANSYS Fluent, in which the rotor is represented by source terms in the Navier-Stokes equations, determined by an in-house code; the model was used to evaluate the performance of different wind turbine configurations.In the course of the research an in-house, empirical tip loss correction was proposed, taking into account the influence of the diffuser. The performed study permitted to observe, among others, that moving the rear rotor towards the outlet of the diffuser may result in a reduction of the wind speed through the front rotor, placed at the inlet to the diffuser, and a decrease in the overall system power
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Wing, Eliya. "Numerical simulation of ice accretion on 3-D rotor blades." Thesis, Georgia Institute of Technology, 2014. http://hdl.handle.net/1853/51833.
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Rotorcraft vehicles are highly sensitive to ice accretion. When ice forms on helicopter rotor blades, performance degradation ensues due to a loss of lift and rise in drag. The presence of ice increases torque, power required, and leads to rotor vibrations. Due to these undesirable changes in the vehicle's performance, the FAA requires intensive certification to determine the helicopter’s airworthiness in icing conditions. Since flight tests and icing tunnel tests are very expensive and cannot simulate all conditions required for certification, it is becoming necessary to use computational solvers to model ice growth and subsequent performance degradation. Currently, most solvers use the strip theory approach for 3D shapes. However, rotor blades can experience significant span-wise flow from separation or centrifugal forces. The goal of this work is to investigate the influence of span-wise flow on ice accretion. The classical strip theory approach is compared to a curved surface streamline based approach to assess the relative differences in ice formation.
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Belko, Milan. "Součinitele přestupu tepla na parou obtékaných plochách parních turbín." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2013. http://www.nusl.cz/ntk/nusl-230763.
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This thesis in introductory part aims to analyze the available literature on the heat transfer coefficient in labyrinth seals and rotating discs of steam turbines. The available experiment studies were processed to summarize heat transfer coefficients on the rotating parts of the turbine. Then, this thesis specifies a design calculation to determine the heat transfer coefficient in selected parts of the turbine, exercisable for specific geometric and operating parameters. The outcome of this work is simulation of rotor dilation of operating steam turbine in the program Ansys during cold start of turbine.
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Bernabè, Matteo. "Multi-rotor aircraft flying qualities assessment by means of inverse simulation." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2018. http://amslaurea.unibo.it/15910/.
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This thesis work wants to investigate in how complex the mathematical model of a multi-rotor drone has to be, in order to simulate three different flight conditions: impulsive responses, vertical and horizontal flight.
This is done by exploiting a technique called inverse simulation.
Also the two autopilot used to control the model has been designed to be as close as possible to the real one.
The results obtained with Simulink are then compared with the telemetry data collected during the real flight by the Pixhawk flight controller.
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Novinschi, Anca. "Simulation and implementation of rotor flux control for an induction motor." Thesis, De Montfort University, 1998. http://hdl.handle.net/2086/5208.
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Zhao, Jinggen. "Dynamic Wake Distortion Model for Helicopter Maneuvering Flight." Diss., Georgia Institute of Technology, 2005. http://hdl.handle.net/1853/7103.
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A new rotor dynamic wake distortion model, which can be used to account for the rotor transient wake distortion effect on inflow across the rotor disk during helicopter maneuvering and transitional flight in both hover and forward flight conditions, is developed. The dynamic growths of the induced inflow perturbation across the rotor disk during different transient maneuvers, such as a step pitch or roll rate, a step climb rate and a step change of advance ratio are investigated by using a dynamic vortex tube analysis. Based on the vortex tube results, a rotor dynamic wake distortion model, which is expressed in terms of a set of ordinary differential equations, with rotor longitudinal and lateral wake curvatures, wake skew and wake spacing as states, is developed. Also, both the Pitt-Peters dynamic inflow model and the Peters-He finite state inflow model for axial or forward flight are augmented to account for rotor dynamic wake distortion effect during helicopter maneuvering flight. To model the aerodynamic interaction among main rotor, tail rotor and empennage caused by rotor wake curvature effect during helicopter maneuvering flight, a reduced order model based on a vortex tube analysis is developed.
Both the augmented Pitt-Peters dynamic inflow model and the augmented Peters-He finite state inflow model, combined with the developed dynamic wake distortion model, together with the interaction model are implemented in a generic helicopter simulation program of UH-60 Black Hawk helicopter and the simulated vehicle control responses in both time domain and frequency domain are compared with flight test data of a UH-60 Black Hawk helicopter in both hover and low speed forward flight conditions.
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Hanson, Berenike. "Investigation of a non-uniform helicopter rotor downwash model." Thesis, Linköping University, Department of Electrical Engineering, 2008. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-17193.
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This master thesis was carried out at the Department of Aerodynamics and Flight Mechanics at Saab Aerosystems, Linköping, Sweden. It makes up the author’s final work prior to graduation in the field Applied Physics and Electrical Engineering at the Department of Electrical Engineering at The Linköping Institute of Technology (LiTH), Linköping, Sweden.
The objective of the paper was to study a non-uniform helicopter rotor downwash model in forward flight for the unmanned helicopter Skeldar, which is under development at Saab. The main task was to compare the mentioned model with today’s uniform downwash model in order to find differences and similarities. This was done both from a modeling and a controlling perspective. To start with, an introduction is given which is followed by a helicopter theory chapter. The following three chapters deal with the theory of induced velocity, the helicopter model and the Linear Quadratic Regulator (LQR). Finally, the results are presented and discussed.
The downwash models were derived using Momentum Theory (MT) and Blade Element Theory (BET). These two theories were combined in order to find a connection between the induced velocity and the rotor thrust coefficient. The non-uniform downwash model that was studied is proposed by Pitt & Peters and describes a linear variation of the induced velocity in the longitudinal plane.
For the control, a LQ-regulator was chosen since it is easily implemented in MATLAB and it stabilizes the plant model by feedback and consequently creates a robust system. Before the controller could be implemented, the models had to be reduced and the states had to be divided into longitudinal and lateral ones.
The comparison between the open systems clearly shows that differences in the inflow models propagate to all states and consequently the helicopter behaves differently in all planes. Great discrepancies are apparent for the angular velocities p and q. For Pitt & Peters’ model those states are believed to be strongly affected by the system’s positive real pole, causing a rather unstable behavior. When the systems were closed by feedback, the differences were reduced dramatically. Pitt & Peters’ model resulted in greater overshoots than the uniform model, but the overall behavior of all states was rather similar for the two models.
It is concluded, that the adaption of Pitt & Peters’ inflow model does not make any substantial difference when a controller is implemented. The differences between the open systems, however, are reason enough to question Pitt & Peters’ model. In order to evaluate the non-uniform model properly, it has to be compared to suitable flight data which is still lacking up to this date.
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Weissenfels, Robert D. "Full nonlinear simulation of helicopter coupled rotor-fuselage motion using MATLAB Symbolic processor and dynamic simulation." Thesis, Monterey, California. Naval Postgraduate School, 2000. http://hdl.handle.net/10945/9390.
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This thesis formulates the full nonlinear equations of motion for determining the stability of helicopter coupled rotor-fuselage motion utilizing MATLAB(registered)'s Symbolic Math Toolbox. Using the extended symbolic processor toolbox, the goal of this work was to eliminate the time consuming process of convening Fortran or C code generated by the symbolic processor, MAPLE(registered) into a MATLAB(registered) useable format where it is further incorporated into an S-function' to be used in the dynamic simulation environment. The formulation of the equations of motion utilized in this process is unique in that it uses the complete set of nonlinear terms in the equations of motions without utilizing ordering schemes, small angle assumptions, linearizing techniques, or other simplifying assumptions. After derivation, the equations of motion are numerically integrated using the dynamic simulation software SIMULINK(registered) and a time history plot is generated of blade and fuselage motion. The equations of motion are regenerated with each time step allowing the adjustment of characteristic structural, blade and dampening properties. These time traces can be used to explore the effects of damping nonlinearities, structural nonlinearities, active control, individual blade control, and damper failure on ground resonance.
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Johansson, Helena. "Investigation of rotor downwash effects using CFD." Thesis, Linköping University, Department of Electrical Engineering, 2009. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-17651.
Full textAbstract:
This paper is the result of a master thesis project on helicopter rotor downwash effects using computational fluid dynamics (CFD). The work was performed at the department of Aerodynamics and Flight Mechanics at Saab AB, Linköping in 2008. It completes the author’s studies for a M.Sc degree in Applied Physics and Electrical Engineering at the Department of Electrical Engineering at the Linköping institute of technology (LiTH), Linköping, Sweden.
The aim of the project was to study the rotor downwash effects and its influence on the helicopter fuselage. To fulfil this purpose, several CFD calculations were carried out and the aerodynamic forces and moments resulting from the calculations were implemented in an existing simulation model, developed in-house at Saab. The original (existing) model was compared to the updated model by studying step responses in MATLAB, Simulink. For some step commands, the comparisions indicated that the updated model was more damped in yaw compared to the original model for the hovering helicopter. When the helicopter was trimmed for a steady turn, the states in the updated model diverged much faster than the states in the original model for any given step command.
In order to investigate the differences between the original helicopter model and the updated model from a controlling perspective, a linear quadratic (LQ) state feedback controller was synthesized to stabilize the vehicle in a steady turn. The LQ method was chosen as it is a modern design technique with good robustness and sensitivity properties and since it is easily implemented in MATLAB. Before synthesising, a simplification of the helicopter model was made by reducing states and splitting them into lateral and longitudinal ones. Step responses from simulations with the original and the updated model were studied, showing an almost identical behavior.
It can be concluded that the aerodynamic coefficients obtained from the CFD calculations can be used for determining the aerodynamic characteristics of the helicopter. Some further validation is needed though, for example by comparing the results with flight test data. In order to build an aerodynamic data base that covers the whole flight envelop, additional CFD calculations are required.
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Durajová, Věra. "Numerická simulace navařování rotoru turbíny." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2010. http://www.nusl.cz/ntk/nusl-229341.
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The project elaborated in frame of engineering studies, solves the problem of restoration of the damaged hinge groove blades, and the surfacing of cylindrical faces of the SAW method, using additional material TOPCORE 838 B. The turbine rotor is made from steel with high resistance temperature 30CrMoNiV5-11. Based on literature studies and issues surfacing calculation, it was established that will preheat the material. The issue was solved by using simulation program SYSWELD.
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Noronha, Roberto F. de. "Simulation and detection of transverse cracks in rotors." Thesis, Cranfield University, 1989. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.352953.
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Ilie, Katherine-Rodica, and Katherine ilie@rmit edu au. "Modelling, Simulation and Optimisation of Asymmetric Rotor Profiles in Twin-screw Superchargers." RMIT University. Aerospace, Mechanical and Manufacturing Engineering, 2007. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20080213.144857.
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There is a growing recognition worldwide of the need for more powerful, smaller petrol engines, capable of delivering the higher picking power of larger engines, yet still being economical and environmentally friendly when used for day-to-day driving. An engineering solution for more efficient engines has been considered by research so far. It has been identified that superchargers can potentially improve the performance of automotive engines; therefore research has focused on developing superchargers and supercharger components with higher efficiency. Of particular interest to the research presented in this thesis has been the twin-screw supercharging compressor with design adapted for automotive use (the twin-screw supercharger). The performance of this supercharger type depends on the volume and total losses of the air flow through the supercharger rotors more than on any other aspects of its behaviour. To accurately predict the efficiency of the twin-screw su percharger for matching a particular engine system, accurate supercharger design is required. The main objective of this research was the investigation of the existing limitations of twin-screw superchargers, in particular leakage and reduced efficiency, leading to the development of optimal asymmetric rotor profiles. This research has been completed in four stages defining an innovative rotor design method. The parametric three-dimensional geometric model of twin-screw supercharger rotors of any aspect ratio was developed. For model validation through visualisation, CAD rotor models with scalable data were generated in commercial CAD software and calibrated experimentally by Laser Doppler Velocimetry (LDV) tests. Calibrated rotor profile data can be transferred into CAD-CFD interface for flow simulation and performance optimisation. Through the application of this new rotor design method, new opportunities are created for the twin-screw supercharger design practice, making it a part of the engineering solution for more efficient engines.
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POMMIER, THOMAS JEAN BERNARD. "Validation of CFD simulation with PIV measurements for Open Rotor Noise Predictions." Thesis, KTH, Mekanik, 2015. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-170779.
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CROR means Contra--‐Rotating Open Rotor. Its efficiency is better than usual in aeronautics thanks to its geometry (open rotor and thus high bypass ratio) but also by adding a second rotor. Indeed it enables to recover the swirl loss of the first rotor. However, this engine is rarely used today in civil aviation for acoustic reasons. Studies are carried out in order to reduce its noise emissions. One of its biggest sources is the interaction between both rotors with the impact of first rotor wake on second rotor blades. This report focuses on the aerodynamics of this wake. The goal is to quantify CFD uncertainties comparing them to wind tunnel testing results. PIV (Particle Image Velocimetry) and hot--‐wire measurements were carried out by a team located in Bremen, Germany. They obtained flow mean and turbulent velocities. I was in charge of CFD simulations, processed with RANS equations and two turbulence models. But most of my work was to post--‐process both CFD and wind tunnel testing results with Python Programming and then compare them. In addition, other effects on these mean and turbulent velocities are studied in this report: test variability, blade--‐to--‐blade variability, transition effect and rpm effect.
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Bridel-Bertomeu, Thibault. "Investigation of unsteady phenomena in rotor/stator cavities using Large Eddy Simulation." Thesis, Toulouse, INPT, 2016. http://oatao.univ-toulouse.fr/17867/1/BRIDEL_BERTOMEU.pdf.
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This thesis provides a numerical and theoretical investigation of transitional and turbulent enclosed rotating flows, with a focus on the formation of macroscopic coherent flow structures. The underlying processes are strongly threedimensional due to the presence of boundary layers on the discs and on the walls of the outer (resp. inner) cylindrical shroud (resp. shaft). The complexity of these flows poses a great challenge in fundamental research however the present work is also of importance for industrial rotating machinery, from hard-drives to space engines turbopumps - the design issues of the latter being behind the motivation for this thesis. The present work consists of two major investigations. First, industrial cavities are modeled by smooth rotor/stator cavities and therein the dominant flow dynamics is investigated. For the experimental campaigns on industrial machinery revealed dangerous unsteady phenomena within the cavities, the emphasis is put on the reproduction and monitoring of unsteady pressure fluctuations within the smooth cavities. Then, the LES of three configurations of real industrial turbines are conducted to study in situ the pressure fluctuations and apply the diagnostics already vetted on academic problems.
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Steinbrecher, Christian. "Numerische Simulation eines berührungsfrei gelagerten Rotors für eine Blutpumpe." [S.l.] : [s.n.], 2004. http://deposit.ddb.de/cgi-bin/dokserv?idn=974166618.
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Deans, Collin Andrew. "Simulation and Integration of a 6-DOF Controllable Multirotor Vehicle." Thesis, Virginia Tech, 2020. http://hdl.handle.net/10919/99629.
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The purpose of this thesis is to develop an existing design of a fully controllable multi-rotor vehicle toward simulating small satellite dynamics, enabling technology development to be accelerated and component failure risks to be mitigated by providing a testing platform with dynamics similar to those of small satellites in orbit. Evaluating dynamics-sensitive software and hardware components for use in small satellite operations has typically been relegated to simulated or physically constrained testing environments. More recently, researchers have begun using multi-rotor aerial vehicles to mimic the orbital motion of such satellites, further increasing simulation fidelity. The dynamical nature of multi-rotor vehicles allows them to accurately simulate the translational dynamics of a small satellite, but they struggle to accurately simulate rotational dynamics, as conventional multi-rotor vehicles' translational and rotational dynamics are coupled. In this thesis, an optimal design for a multi-rotor vehicle independently controllable in all six degrees of freedom is evaluated as a suitable simulation platform. The design of the proposed physical system is discussed and progress toward its construction is demonstrated. To facilitate future research endeavors, a simulation of the vehicle in a software-in-the-loop environment, using the Gazebo dynamics simulator, is developed and its performance evaluated. This simulation is then used to evaluate the vehicle's feasibility as a small-satellite dynamics simulator by tasking it with tracking dynamic position and attitude time histories representative of a small satellite.Master of Science
When developing a spacecraft, it can be difficult to accurately test software and hardware that are sensitive to the spacecraft's motion. This difficulty arises because the space environment experienced by orbiting spacecraft allows them to move and rotate freely, and recreating this freedom of motion on earth requires large, expensive, and difficult-to-access test equipment. To make this testing more accessible, researchers have begun using quadcopter drones to mimic some aspects of a spacecraft's motion. While quadcopters can move like an orbiting spacecraft can, their designs do not allow them to rotate like an orbiting spacecraft can, thus providing an incomplete recreation of spacecraft motion. To correct this shortcoming, an existing drone design that is able to move and rotate simultaneously without fear of crashing is developed, with progress shown toward its construction. A software simulation of the drone is developed to help future researchers test software and algorithms before flying it on the physical drone. The simulation is then used to see how well the drone design can recreate the motions that a small spacecraft would experience.
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Pekarovič, Ján. "Realizace vrtulníku se čtyřmi rotory." Master's thesis, Vysoké učení technické v Brně. Fakulta elektrotechniky a komunikačních technologií, 2014. http://www.nusl.cz/ntk/nusl-220957.
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This thesis deals with the design of a helicopter with four rotors known as quadcopter. It describes the principles of operation and existing modifications. Part of the work is the selection of a suitable frame, remote control set, engines and propellers, battery, sensors for stabilization and detection of obstacles and microcontroller for their operation. The paper presents the concept of the specific copter design, design and simulation of printed circuit boards to their self-production, activation and testing. The final part of the thesis includes an economic assessment of the project and its comparison with competitors.
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Joulain, Antoine. "Simulation aérodynamique d'extrémités de pales de rotors sustentateurs d'hélicoptère." Thesis, Aix-Marseille, 2015. http://www.theses.fr/2015AIXM4768.
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L’aérodynamique de l’hélicoptère est fortement impactée par les tourbillons générés aux extrémités de pales. La complexité des phénomènes en jeux et l’insuffisance de données expérimentales locales font du design d’extrémité un véritable défi. Cette étude propose une nouvelle approche dédiée à l’étude des extrémités en vol stationnaire. Une méthode numérique rapide et précise est mise au point afin d’étudier une extrémité de pale en rotation comme une extrémité d’aile fixe. Chaque étape de la construction de la méthode est validée par des comparaisons détaillées avec des données expérimentales publiées. Le code CFD elsA est dans un premier temps utilisé pour mettre en place une méthode de calcul basée sur la résolution des équations Reynolds-Averaged Navier-Stokes en stationnaire. La convergence de la solution et l’indépendance au maillage et aux paramètres numériques sont étudiées en détail en deux, puis en trois dimensions. La précision importante de la solution numérique permet d’analyser finement la physique de l’enroulement tourbillonnaire en extrémité. Des géométries tronquée et arrondie sont étudiées en détail, et révèlent la présence de systèmes tourbillonnaires complexes. Puis la nouvelle méthode d’adaptation pale en rotation / aile fixe est présentée. Une méthode de calcul hybride est mise au point entre le code de mécanique du vol HOST et le code elsA. En repère fixe, l’aérodynamique globale sur la pale et locale en extrémité est calculée fidèlement pour toutes les configurations étudiées. Comparée aux méthodes d’adaptation précédemment publiées, cette nouvelle stratégie offre une amélioration considérable concernant la simulation de l’aérodynamique de paleHelicopter aerodynamics is strongly influenced by the vortices generated from the rotor-blade tips. The design of efficient tip shapes is a challenging task because of the complexity of the aerodynamic phenomena involved and the lack of local blade-tip flow measurements. This work provides a contribution to the design of helicopter tips in hover. An efficient, relatively simple and quick numerical method is set up to study rotating blade tips in fixed-wing configurations. The accuracy of the method is shown at each step of the construction by comprehensive comparisons with reliable experimental data from the literature. First, an efficient steady Reynolds-Averaged Navier-Stokes method is constructed using ONERA's elsA code. Comprehensive studies of convergence, grid dependence and sensitivity to the numerical method are performed in two and three dimensions. The very good agreement of the solution with measurements and the accuracy of the numerical method allow a physical analysis with unprecedented detail of the vortex generation and roll-up near square and rounded wing tips. The new methodology of framework adaptation is then presented. An uncoupled hybrid strategy is set up using AIRBUS HELICOPTERS' Comprehensive Analysis code HOST and the Computational Fluid Dynamics solver elsA. Global and local performance calculations are validated for all investigated test cases. Comparison with previously published adaptation methods indicates considerable improvement in the prediction of the blade aerodynamics
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Zaki, Afifa Adel. "Using tightly-coupled CFD/CSD simulation for rotorcraft stability analysis." Diss., Georgia Institute of Technology, 2012. http://hdl.handle.net/1853/43579.
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Dynamic stall deeply affects the response
of helicopter rotor blades, making its modeling accuracy very important. Two commonly used dynamic stall models were implemented
in a comprehensive code, validated, and contrasted to provide improved analysis
accuracy and versatility. Next, computational fluid dynamics and computational structural dynamics loose coupling methodologies are reviewed, and a general tight coupling approach was implemented and tested. The tightly coupled
computational fluid dynamics and computational structural dynamics methodology is then used to assess the stability characteristics of complex rotorcraft problems. An aeroelastic analysis of rotors must include an assessment of
potential instabilities and the determination of damping ratios for all modes of interest. If
the governing equations of motion of a system can be formulated as linear, ordinary
differential equations with constant coefficients, classical stability evaluation
methodologies based on the characteristic exponents of the system can rapidly and
accurately provide the system's stability characteristics. For systems described by linear,
ordinary differential equations with periodic coefficients, Floquet's theory is the preferred
approach. While these methods provide excellent results for simplified linear models with
a moderate number of degrees of freedom, they become quickly unwieldy as the number
of degrees of freedom increases. Therefore, to accurately analyze rotorcraft aeroelastic
periodic systems, a fully nonlinear, coupled simulation tool is used to determine the
response of the system to perturbations about an equilibrium configuration and determine
the presence of instabilities and damping ratios. The stability analysis is undertaken using
an algorithm based on a Partial Floquet approach that has been successfully applied with
computational structural dynamics tools on rotors and wind turbines. The stability analysis approach is computationally
inexpensive and consists of post processing aeroelastic data, which can be used with any
aeroelastic rotorcraft code or with experimental data.
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Barbosa, Emerson. "Etude numérique des écoulements tridimensionnels dans des cuves cylindriques rotor-stator." Phd thesis, Université d'Evry-Val d'Essonne, 2002. http://tel.archives-ouvertes.fr/tel-00354646.
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L'écoulement d'un fluide visqueux incompressible dans une cuve cylindrique rotor-stator est étudié. Ces écoulements ont fait l'objet de récents travaux numériques tridimensionnels pour des rapports d'aspect h>1,75. On propose une étude numérique de la rupture de l'axisymétrie de l'écoulement dans une cavité de rapport d'aspect réduit (h=1 et 1,5) et des nombres de Reynolds Re<8500. Les équations de Navier-Stokes sont résolues par un code vitesse-pression en coordonnées cylindriques qui repose sur des méthodes aux différences finies du second ordre. Deux approches numériques sont mises en œuvre pour mener cette investigation. L'une consiste à linéariser les équations autour d'un écoulement de base axisymétrique stationnaire. Les conditions initiales résultent de la superposition de l'écoulement de base et d'une perturbation aléatoire. Cette analyse de stabilité linéaire permet de déterminer le premier seuil de criticalité et met en évidence le mode azimutal kc le plus instable. L'autre consiste à intégrer les équations du mouvement avec différentes conditions initiales: (i) soit un écoulement de base axisymétrique stationnaire perturbé aléatoirement, (ii) soit un état où le fluide est au repos, (iii) soit un régime établi trouvé pour une autre valeur de Re. L'analyse de stabilité non-linéaire (i) montre que le développement d'un mode kc est responsable d'une bifurcation de Hopf super-critique lorsque Re dépasse une première valeur critique. L'écoulement de base bascule alors vers des solutions instationnaires de période T, dont les caractéristiques spatiales dépendent de la valeur de kc. L'axisymétrie de l'écoulement n'est brisée que lorsque kc est non nul. Dans ce cas, les solutions super-critiques sont des ondes qui exhibent une invariance par rotation d'angle 2pi/kc autour de l'axe et qui tournent avec une période azimutale TRWkc=kc*T. L'écoulement subit ensuite d'autres bifurcations et les caractéristiques spatio-temporelles des ondes tournantes bifurquées sont présentées en détails. L'utilisation d'autres conditions initiales (ii)-(iii) met en évidence des branches de solutions multiples: il apparaît que la convergence vers l'une ou l'autre des solutions possibles dépend de la façon dont est répartie l'énergie cinétique de départ.
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Batailly, Alain. "Simulation de l'interaction rotor/stator pour des turbo-machines aéronautiques en configuration non-accidentelle." Phd thesis, Ecole centrale de nantes - ECN, 2008. http://tel.archives-ouvertes.fr/tel-00364945.
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Dans le cadre de la conception de turbo-machines aéronautiques, l'amélioration du rendement est assurée, entre autres, par la diminution du jeu fonctionnel entre les parties tournantes et statiques, telles que les roues aubagées et le carter qui les entoure. Cette stratégie a des conséquences sur le comportement vibratoire des turbo-machines en favorisant l'apparition de contacts structuraux entre les sommets d'aubes et le carter, par exemple. Lorsque plusieurs points de contact co-existent, des phénomènes d'interaction modale peuvent apparaître. La simulation de ces phénomènes, potentiellement dangereux, dans un cadre indutriel est au cœur de notre étude. Du fait de la dimension du problème à traiter, des méthodes de réduction modale sont utilisées : une méthode à interfaces fixes, la méthode de Craig-Bampton, et une méthode à interfaces libres, la méthode de Craig-Martinez. L'étude porte notamment sur la performance de ces méthodes de réduction lorsqu'elles sont associées à une non linéarité de type contact. Le phénomène d'interaction modale est tout d'abord étudié sur des modèles 2D simplifiés avec l'analyse de la sensibilité des régimes d'interaction à la taille des modèles réduits, puis sur les modèles 3D industriels pour lesquels la solution vraie n'est pas accessible. La gestion du contact dans le 3D fait appel aux B-splines bicubiques surfaciques afin d'assurer de meilleures propriétés à la surface de contact et de faciliter la résolution numérique. Les résultats obtenus à l'aide des deux méthodes de réduction modale sont comparés et permettent de déterminer la méthode la plus appropriée pour l'industrialisation du code présentée en annexe de ce mémoire.
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Queguineur, Matthieu. "Stability and control of unsteady phenomena in rotor/stator cavities using Large Eddy Simulation." Thesis, Toulouse, INPT, 2020. http://www.theses.fr/2020INPT0043.
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Les phénomènes instationnaires dans les cavités rotor/stator sont connus pour être la source de dangereuses vibrations dans les turbopompes spatiales. Bien que plusieurs mesures palliatives aient été prises en comptes durant les phases de conception, des campagnes d’essais ont mis en évidence de fortes oscillations des écoulements internes pouvant menacer le moteur cryogénique des lanceurs. Aujourd’hui, l’origine de ce phénomène, appelé «bandes de pression », est peu compris et difficile à prédire numériquement. L’objectif de cette thèse est d’analyser les mécanismes physiques de ce phénomène afin d’apporter des solutions pour le contrôler. Pour répondre à cette problématique, deux types de configuration sont étudiés: une cavité rotor/stator annulaire et une cavité de turbopompe spatiale. Les couches limites tournantes dans ces cavités sont connues pour être 3D et réceptives à plusieurs types d’instabilités prenant entre autre la forme de spirales ou d’anneaux. Les simulations basées sur la moyenne de Reynolds (RANS) ont par le passé échoué à prédire ce type d’écoulement. Cependant, les Simulations aux Grandes Echelles (SGE) se sont avérées être une alternative à ce problème et sont donc été utilisées tout au long de cette thèse. Des Densités Spectrales de Puissance (DSP) ainsi que des Décompositions modales dynamiques (DMD) appliqués aux résultats SGE, ont permis de montrer que le phénomène de bandes de pression est visible également dans une cavité annulaire de type académique et composé de trois modes dictant toute la dynamique du système. Afin d’étudier les interactions de ces modes, une nouvelle méthode appelée Dynamic Mode Tracking/Control (DMT/DMTC) a été proposée durant cette these. La DMT est construite pour extraire des structures cohérentes dans une simulation SGE. De plus, en ajoutant un terme de relaxation dans les équations de Navier-Stokes couplées avec la DMT, sa variante appelée DMTC permet de contrôler et de suivre en temps réelle un ou plusieurs modes et donc de pouvoir analyser de possibles interactions. Appliqué à la cavité académique annulaire, cette méthode a permis de montrer que le mode basse fréquence est généré dans l’écoulement par le mode dominant du système. Pour aller plus loin, des analyses de stabilité linéaire de type global (GLSA), sont effectuées sur la cavité académique. Grâce à des méthodes adjointes, la GLSA a permis de mettre en avant l’origine spatiale de chacun des trois modes. Deplus, afin de mettre en place des stratégies de contrôle, la sensibilité à la modification de l’écoulement de base, obtenue par GLSA, a permis d’identifier la région à modifier pour stabiliser un mode donné ou décaler sa fréquence. Appliqué au cas académique, il est montré et que contrôler la couche limite du stator est le moyen le plus efficace de supprimer le phénomène de bandes de pression à travers des injections/aspirations. Pour finir, le phénomène de bandes de pression est analysé dans une cavité de turbopompe spatiale. En particulier, la sensibilité de ce phénomène aux changements géométriques est abordée à travers deux configurations: une première sans les aubes du stator de la turbopompe et une deuxième avec. Bien que les aubes génèrent un écoulement complexe, des fréquences similaires de fluctuation de pression sont retrouvées dans les deux configurations avec cependant des nombres azimutaux caractéristiques différents. En se basant sur les études faites sur la cavité académique, une version adaptée de GLSA pour la dynamique de la turbopompe permet de mettre en avant que malgré que le phénomène de bandes pression soit particulièrement présent dans la veine de la turbopompe, la source de ces modes se situe dans les cavités inférieures entre le rotor et le stator. De plus les résultats de GLSA mettent en avant que deux moyens de contrôle pourraient être appliqués pour supprimer le phénomène de bandes de pression dans ce cas industriel: modifier le joint d’étanchéité ou modifier la fuite du moyeuUnsteady phenomena in rotor/stator cavity are well known to be the source of dangerous vibrations in space turbopump. Even though many palliative measures have been taken during their design, experimental campaigns often reveal high flow oscillations that can jeopardize turbomachinery components and even the rocket engine. Today, the origin of such flow instabilities usually called ’pressure band phenomenon’(PBP) is not well understood and difficult to predict numerically. The main goal of this thesis is to investigate such phenomenon mechanism to find technical solutions so as to control it. This problematic is addressed here trough two types of configuration: an academic rotor/stator cavity and a space turbopump cavity. When it comes to cavity flows, their rotating boundary layers are known to be three dimensional and receptive to several instabilities taking the form of spirals or annuli. Reynolds Averaged Navier-Stokes Simulations (RANS)failed to predict such unsteady systems. However, Large Eddy Simulation (LES) proved to be a relevant alternative in many similar applications and is therefore chosen for the present work. Using Power Spectral Analysis (PSD) and Dynamic Mode Decomposition (DMD) on LES predictions, one shows that the PBP is retrieved in an annular smooth rotor/stator cavity and it is composed of three modes driving all the system dynamics. To investigate these mode organization and their possible interactions, a new tool called Dynamic Mode Tracking /Control (DMT/DMTC) is introduced. DMT is constructed so as to extract "on-thefly" flow coherent structures with a given frequency on the basis of LES. Furthermore, augmenting the Navier-Stokes equations with a relaxation term coupled to DMT, DMTC allows to control and follow the evolution of a controlled mode as well as non controlled ones and thereby observe interactions. This strategy after validation is applied to the annular rotating cavity and shows that the low frequency mode is generated by the dominant mode of the system. To go further, Global Linear Stability Analysis (GLSA) augmented with adjoint methods is used to shed some light on all mode origins and points out that the low frequency and dominant modes are coming from the stationary boundary layer. In order to set up control strategies, the GLSA framework is further developed introducing the concept of the sensitivity to base flow modifications which gives the location where the flow should be modified if one wants to stabilize or at least shift a frequency mode. Applied to the academic cavity, one shows that contrary to most studies in the literature, controlling the stator boundary layer is the more efficient way to damp the PBP through suction/injection devices. Finally, gathering all the previous understanding of this flow, the LES framework enables to validate the control strategies proposed and to stabilize the PBP for very low suction amplitudes. To finish, the PBP is analyzed in real space turbompump cavities. In particular, the sensitivity of this specific phenomenon to geometry changes is investigated through two configurations: one without and one with the blades of the stator of the turbopump. Even though the introduction of the blades in the LES creates a more complex flow with the presence of shocks, similar pressure fluctuation spectra are retrieved in both configurations but with azimuthal wavenumber modes that are shifted. Following the studies on the academic cavity, an adapted GLSA to the non-linear dynamics of the turbopump enables to point out that even though the PBP modes are particularly marked in the mainstream of the system, the source of these modes is located in the subcavity in the rotor-stator wheel space. In particular, GLSA results indicate that two possible ways to control the phenomenon are possible: modifying the flow around the seal rim and or modifying the leak around the hub