Auswahl der wissenschaftlichen Literatur zum Thema „Pales de rotor“
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Zeitschriftenartikel zum Thema "Pales de rotor"
Maïzi, Mohamed, Rabah Dizène und Ouahiba Guerri. „Simulation instationnaire de l’écoulement autour d’un rotor éolien à axe horizontal“. Journal of Renewable Energies 15, Nr. 4 (25.10.2023): 599–608. http://dx.doi.org/10.54966/jreen.v15i4.349.
Der volle Inhalt der QuelleGedikli, Hasan, und İsmail Özen. „Investigation of Solid Particle Erosion Behaviour on Erosion Shield of a Helicopter Rotor Blade“. Pamukkale University Journal of Engineering Sciences 26, Nr. 1 (2020): 68–74. http://dx.doi.org/10.5505/pajes.2019.82150.
Der volle Inhalt der QuelleDAL, Abdurrahim, und Tuncay Karaçay. „Effect of surface roughness of a radial aerostatic bearing on the load carrying capacity of a rotor-bearing system“. Pamukkale University Journal of Engineering Sciences 23, Nr. 4 (2017): 383–89. http://dx.doi.org/10.5505/pajes.2017.03274.
Der volle Inhalt der QuelleGROTELUSCHEN, FRANK. „PROGRESOS EN LA FABRICACIÓN DE PALAS DE ROTOR“. DYNA INGENIERIA E INDUSTRIA 92, Nr. 1 (2017): 126. http://dx.doi.org/10.6036/8207.
Der volle Inhalt der QuelleCusme- Mercado, Luís G., Alvez R. Mera- Mosquera, Franklin A. Ochoa- González, Galo E. Maldonado- Ibarra und Lenin Montaño- Roldan. „Caracterización experimental de una turbina eólica para vivienda unifamiliar“. Dominio de las Ciencias 4, Nr. 3 (31.07.2018): 29. http://dx.doi.org/10.23857/dc.v4i3.792.
Der volle Inhalt der QuelleRíos Villacorta, Alberto. „ANÁLISIS COMPARATIVO DE LOS MODELOS DINÁMICOS DE UNA TURBINA EÓLICA DE VELOCIDAD FIJA“. Ingenius, Nr. 15 (04.07.2016): 37. http://dx.doi.org/10.17163/ings.n15.2016.04.
Der volle Inhalt der QuelleGüneş, Doğan, und Ergin Kükrer. „Performance Rating and Flow Analysis of an Experimental Airborne Drag-Type VAWT Employing Rotating Mesh“. Computation 12, Nr. 4 (08.04.2024): 77. http://dx.doi.org/10.3390/computation12040077.
Der volle Inhalt der QuelleBuenger, Victoria. „The dark side of the workplace: Managing incivilityAnnette B. Roter, New York: Routledge, 2019, 172 pages, $44.95 paperback.“ Personnel Psychology 73, Nr. 3 (07.08.2020): 549–50. http://dx.doi.org/10.1111/peps.12396.
Der volle Inhalt der QuelleTomboravo, Delphin, Elodie Francia Siaka, Jeannot Velontsoa, Roger Vony und Tsialefitry Aly Saandy. „Contrainte électrique majeure d’une génératrice synchrone à rotor bobiné associée à un aérogénérateur chargé et influence de rayon de pales sur la vitesse du vent au démarrage du groupe“. Entropie : thermodynamique – énergie – environnement – économie 3, Nr. 2 (2022). http://dx.doi.org/10.21494/iste.op.2022.0863.
Der volle Inhalt der QuellePorras, Jefferson, Luis Navarrete, Jorge Ramírez und Sebastián Paredes. „Diseño de una turbina eólica espiral de arquímedes mediante software cad - cae“. LATAM Revista Latinoamericana de Ciencias Sociales y Humanidades 4, Nr. 3 (16.09.2023). http://dx.doi.org/10.56712/latam.v4i3.1125.
Der volle Inhalt der QuelleDissertationen zum Thema "Pales de rotor"
Duran-Venegas, Eduardo. „Modélisation et optimisation d'un rotor à pales flexibles“. Thesis, Aix-Marseille, 2019. http://www.theses.fr/2019AIXM0195.
Der volle Inhalt der QuelleRotors have been historically developed for harvesting and propulsion. For wind turbines and helicopters, decades of research have been done to optimize their design. For recent applications, such as drones, no such a research effort has been made. The high flexibility of the rotor and the different operational conditions still constitute challenging issues for their design. In this work, a coupled fluid-structure model is proposed, taking into account the flexibility of the blades in non-conventional operational conditions.The model is sufficiently simple and robust to permit extensive parameter studies. It includes a model for the wake, a model for the flexible rotor structure and the coupling. Two different wake models are considered: a classical Joukowski model, where two vortices are emitted per blade, one at the tip and one at the axis, and a generalized Joukowski model where the axial vortex is replaced by a hub vortex emitted away from the center. A stability analysis of the solutions derived with the classical Joukowski model is performed. The convective/absolute nature of the instability is analysed for various operational conditions.Stationary wake solutions are used to calculate the flow in the rotor plane. Kutta-Joukowski law and Blade Element Theory are applied to obtain the aerodynamic loads exerted on the blades. The full coupling of the rotor with its wake is first implemented for a rigid configuration. Coupled solutions are obtained for different rotors and compared to experimental and numerical data published in the literature. Finally, blade flexibility is considered using a rod model for the blade
Lebel, Guilhem. „Prévision des charges aéromécaniques des rotors d'hélicoptère : Application aux pales à double flèche“. Thesis, Lyon, INSA, 2012. http://www.theses.fr/2012ISAL0025.
Der volle Inhalt der QuelleNew generation blades have led to new load computation problems due to the evolution of the general shape, with forward and backward sweep. The BlueEdgeTM blade pattented by Eurocopter imposes to reconsider the development methodology and thus it is no longer possible to speak of straight blades and the models used for load computation have to be evaluated. The objective of this thesis is to determine what has to be modified and improved in current load computation methodology in order to reach an acceptable predictive level. This work considers both aerodynamic and dynamic models implemented in the HOST multi-body computer code. The aerodynamics models are based on the hypothesis of a two dimensional flow. The use of the CFD software \emph{elsA} is evaluated. Attention is given to rotor dynamics models that have an impact on loads, such as lead-lag damper models, blade element models and hub models. This thesis presents the different models and gives orientations relating to efficient load computation methodology. The aerodynamics models are compared to windtunnels experiments from the literature. This study leads also to perform flight tests and to investigate the dampers behavior on test benches in order to confront the computed loads to the reality of the helicopter operation. The proposed methodology is able to compute with a good accuracy rotor loads for stabilized flight cases
Roux, Louis. „Modélisation dynamique du départ d'une pale et de la tenue des pales suiveuses dans une turbomachine“. Thesis, Lyon, 2016. http://www.theses.fr/2016LYSEI056.
Der volle Inhalt der QuelleDuring the certification process of a turbo engine, the engine manufacturer has to demonstrate that the loss of a rotor blade does not lead to the "knocking-off" phenomenon, in other words to the cascading failure of the successive blades. Generally, this demonstration is carried out through a costly rig test driving to the partial destruction of the engine. Thanks to the improvement of computational resources, it is now possible to simulate the transient response of the structure subjected to this complex loading. The knowledge of material behavior turns out to be the essential starting point for the simulation. However, only a few studies have been published on the dynamic behavior of nickel-based single crystal superalloys at high temperature reaching 1000°C. With a view to efficiently predicting the consequences of impacts on turbine blades, experimental and numerical works have been conducted on a single crystal frequently used by Turbomeca. High-temperature dynamic compressive tests on Split Hopkinson Pressure Bars (SHPB) have enabled to estimate the material plasticity level and hardening, depending on the crystal orientation, strain rate and temperature. The parameters of a viscoplastic anisotropic law have been identified to effectively model the MC2 macroscopic behavior under highly intense and multiaxial loading. At Safran Snecma Villaroche, ballistic tests have been undertaken on both single crystal plates and blades under high temperatures. In order to consider the fragmentation of profiles in blade-off simulations, a plastic strain criterion depending on stress triaxiality has been calibrated and validated by comparison with the impacts on blades. Post-mortem digital images correlation measurements and high-speed camera recordings have confirmed these simulations. Using LS-Dyna solver, a blade-off modeling strategy has been created and applied to an actual blade-off industrial case. Finally, a rotordynamics approach has been developed and validated with the aim of separately analyzing the primary damage, caused by direct impacts on the first following blades, and the secondary damage due to the effects of unbalance on a flexible rotor
Droz, Christophe. „Guidage des ondes d'ordre élevé dans les composites : application au dégivrage en vol des pales d'hélicoptères“. Thesis, Ecully, Ecole centrale de Lyon, 2015. http://www.theses.fr/2015ECDL0026.
Der volle Inhalt der QuelleWhen helicopters fly through extreme conditions, ice can aggregate on their blades and seriously affect the aircraft performances. Recently, an increasing research effort was devoted to the development of affordable low power de-icing solutions. In this thesis, a wave-based approach is adopted to prevent and/or remove ice aggregates from the surfaces of helicopter rotor blades. The de-icing strategy uses specific high-order guided waves to exceed the shear adhesion strength of ice accretion profiles. Experiments are conducted in order to update the FE model of a realistic rotor blade, then a Model Order Reduction strategy is developed for the Wave Finite Element Method. It involves a projection of the state vectors on a reduced basis of propagating waves shapes, and enables broadband wave analysis in structurally advanced 1D and 2D periodic structures. Guided wave propagation is studied within a helicopter rotor blade, and wave localization and conversion effects are discussed in various 1D and 2D composite waveguides. The interactions of high-order waves with ice aggregates and other types of structural singularities are also examined by means of a Diffusion Matrix Method. Then, time-domain propagation in coupled waveguides subjected to a wave pulse is analysed through a computationally efficient wave-based formulation. Finally, a smart actuator network is designed for the generation of high-order wave pulses and validations are conducted in a composite plate and a Super Puma rotor blade using time simulation
Dubois, Patrick. „Intégration de pales en céramique dans un rotor de microturbine axiale en configuration renversée“. Mémoire, Université de Sherbrooke, 2016. http://hdl.handle.net/11143/9714.
Der volle Inhalt der QuelleTaufik, Atik. „Contribution au développement d'un outil de conception des poutres composites : application aux pales d'hélicoptères“. Toulouse, ENSAE, 1996. http://www.theses.fr/1996ESAE0017.
Der volle Inhalt der QuelleVINCENTI, JEAN. „Etude de l'influence des defauts de pales sur la charge dynamique du rotor et la stabilite de l'helicoptere“. Paris, ENSAM, 1995. http://www.theses.fr/1995ENAM0011.
Der volle Inhalt der QuelleSkladanek, Yan. „Formulation d’un élément fini de poutre pour la dynamique des pales d’hélicoptère de géométrie complexe“. Thesis, Lyon, INSA, 2011. http://www.theses.fr/2011ISAL0122.
Der volle Inhalt der QuelleStructural, shape and performances optimization in helicopter rotor leads to design composite blades initially curved and twisted. This design yields a highly coupled behavior between torsion, longitudinal and bending motions of blades. Besides, dynamic studies of blades have to be performed in the rotational frame, so that all rotatory effects could be siezed by the modeling. A highly accurate non-linear straight beam finite element is proposed to predict the static deformation under aerodynamic and centrifugal loads and achieve dynamic and stability analysis. This elastic model is to be implemented in a comprehensive rotorcraft analysis code, which means accuracy, reliability and calculation time compromise. Model validation is based on analytical, numerical and experimental investigations. The developed model reveals to be very accurate for new blade design including important twist angle and initially curved shape. It is expected to improve prediction quality for full helicopter simulation tools, undergoing strong coupling with advanced aerodynamic model
Aymard, Emmanuel. „Détermination des efforts aérodynamiques s'exerçant sur une surface portante en rotation par une méthodologie basée sur la vélocimétrie laser : application aux pales d'un rotor d'hélicoptère en vol d'avancement“. Aix-Marseille 2, 1998. http://www.theses.fr/1998AIX22113.
Der volle Inhalt der QuelleProulx-Cabana, Vincent. „Algorithmes non-linéaires rapides pour l’aéroélasticité d’ailes rotatives“. Electronic Thesis or Diss., Toulouse, ISAE, 2024. http://www.theses.fr/2024ESAE0001.
Der volle Inhalt der QuelleThis thesis describes the developments of rapid non-linear computational algorithms for rotary-wing aeroelasticity. The main focus of this thesis is the development of the aerodynamic method that is then coupled with a structural solver to produce aeroelastic simulations. For the aerodynamic model, a so called medium fidelity tool based on the potential methods is chosen to capture aerodynamic interactions and phenomenon neglected by the faster low fidelity methods while obtaining the results at a much reduced computational cost compared with the higher fidelity methods based on the Unsteady Reynolds-Averaged Navier-Stokes (URANS) equations. The blades structure is modeled with Euler-Bernoulli beam elements in a Finite Element Method (FEM) to obtain the aeroelastic deflections.The thesis begins with an introduction, followed by an extensive literature review comparison and a small chapter presenting the overarching methodology. Then, the main research objectives are covered in the following chapters and the thesis ends with a conclusion that summarizes the work and presents recommendations. Some optional supplementary materials can be found after the references in the appendices.The main objectives of the thesis are:- Improve the aerodynamic blade loads prediction of a medium fidelity method without increasing significantly the computational cost.- Ensure numerical stability in hover flight, with or without ground effect.- Expose the method sensitivity to its parameters.- Couple the aerodynamic method with a structural method to perform quasi-static blade aeroelasticity simulations.The first objective is obtained with the Unsteady Vortex Lattice Method (UVLM) and its modifications from the classical method to perform rotary wing simulations. The improvement of load predictions is accomplished via non-linear viscous-inviscid coupling (NL-UVLM) that is well known for fixed-wing aerodynamics, but was more rarely used for rotary-wing aerodynamics.The NL-UVLM method is stabilized in hover, especially in ground effect, with the replacement of tightly linked wake panels by free moving particles, namely the Vortex Particles Method (VPM). However, the introduction of vortex particle causes two difficulties: 1) the increase of the computational cost and 2) numerical instability. The first issue is addressed by using the Fast Multipole Method (FMM) to reduce computational complexity. The numerical instability is controlled by adding a Large Eddy Simulation (LES) viscosity. The NL-UVLM-VPM results compare well for the global coefficients, distributed loads and pressure coefficients with many higher fidelity methods and experimental results.The effects of the parameters of the model are explored since they play an important role in its robustness and accuracy. The NL-UVLM-VPM can produce stable and consistent long-time running simulations and obtain results in good agreement with 3D URANS if the parameters are carefully selected.The present work builds upon a previous project that had coupled steady VLM method to a non-linear FEM model to simulate static aeroelasticity of airplane wings. The software is improved to simulate quasi-static rotor blade aeroelasticity. The centrifugal force, necessary for accurate rotary-wing aeroelasticity, is added explicitly as an external force in the FEM. The method is verified compared to other FEM simulations from the literature and the different structural parameters are tested on a simplified single bladed rotor test case. The aeroelastic results are consistent with the expected behavior for each structural parameter. Finally, comparison with the experimental approach developed in the context of this project is presented.The method presented in this work could find applications in rotary-wing, wind turbine and propeller aerodynamic and aeroelastic design while improving the fidelity of flight simulators
Bücher zum Thema "Pales de rotor"
Notebook, leswalkerhanba. Notebook: Cat Pilot Airplane Rotor Crash Children Gift - 50 Sheets, 100 Pages - 6 X 9 Inches. Independently Published, 2020.
Den vollen Inhalt der Quelle findenKonferenzberichte zum Thema "Pales de rotor"
Rehman, A., K. S. Ahmed, F. A. Umrani, B. Munir, A. Mehboob, S. M. Ahmad und Z. Kazmi. „Finite Element Modelling of a Generic Rotor-Bearing System and Experimental Validation“. In ASME 2015 Dynamic Systems and Control Conference. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/dscc2015-9901.
Der volle Inhalt der QuelleBowsher, Aaron, Peter Crudgington, Clayton M. Grondahl, James C. Dudley, Tracey Kirk und Andrew Pawlak. „Pressure Activated Leaf Seal Technology Readiness Testing“. In ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gt2014-27046.
Der volle Inhalt der QuelleHeshmat, Hooshang, James F. Walton, Christopher Della Corte und Mark Valco. „Oil-Free Turbocharger Demonstration Paves Way to Gas Turbine Engine Applications“. In ASME Turbo Expo 2000: Power for Land, Sea, and Air. American Society of Mechanical Engineers, 2000. http://dx.doi.org/10.1115/2000-gt-0620.
Der volle Inhalt der QuelleMessenger, Andrew, Richard Williams, Grant Ingram, Simon Hogg, Stacie Tibos, Jon Seaton und Bernard Charnley. „Experimental and Numerical Development of a Dynamic Clearance Seal for Steam Turbine Application“. In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-56995.
Der volle Inhalt der QuelleHirsch, Jean-François, David Alfano, Paul Cranga, Vincent Gareton und Frédéric Guntzer. „The Blue Edge - Blade Continuation“. In Vertical Flight Society 75th Annual Forum & Technology Display. The Vertical Flight Society, 2019. http://dx.doi.org/10.4050/f-0075-2019-14546.
Der volle Inhalt der QuelleBabin, Cedric, und Fabrizio Fontaneto. „Experimental Characterization of Two Low Aspect Ratio Stages With Scaling Effect for Small Core High Speed Axial Compressor“. In ASME Turbo Expo 2023: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2023. http://dx.doi.org/10.1115/gt2023-103750.
Der volle Inhalt der QuelleLuquet, David, Francois Julienne, Aurélien Arntz und Eric Lippinois. „Evaluation of the Numerical Modelling of a High Pressure Turbine Test Rig“. In ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gt2019-90483.
Der volle Inhalt der QuelleSegon, Fabien, und Aurélien Dupuis. „AIRBUS DS’ HCA: HIGH CAPACITY ACTUATOR FOR SMALL SATELLITE MISSIONS“. In ESA 12th International Conference on Guidance Navigation and Control and 9th International Conference on Astrodynamics Tools and Techniques. ESA, 2023. http://dx.doi.org/10.5270/esa-gnc-icatt-2023-128.
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