Auswahl der wissenschaftlichen Literatur zum Thema „Soufflante de turboréacteur“
Geben Sie eine Quelle nach APA, MLA, Chicago, Harvard und anderen Zitierweisen an
Inhaltsverzeichnis
Machen Sie sich mit den Listen der aktuellen Artikel, Bücher, Dissertationen, Berichten und anderer wissenschaftlichen Quellen zum Thema "Soufflante de turboréacteur" bekannt.
Neben jedem Werk im Literaturverzeichnis ist die Option "Zur Bibliographie hinzufügen" verfügbar. Nutzen Sie sie, wird Ihre bibliographische Angabe des gewählten Werkes nach der nötigen Zitierweise (APA, MLA, Harvard, Chicago, Vancouver usw.) automatisch gestaltet.
Sie können auch den vollen Text der wissenschaftlichen Publikation im PDF-Format herunterladen und eine Online-Annotation der Arbeit lesen, wenn die relevanten Parameter in den Metadaten verfügbar sind.
Zeitschriftenartikel zum Thema "Soufflante de turboréacteur"
LÉWY, S. „MESURE DES SOURCES SONORES DANS UNE MAQUETTE DE SOUFFLANTE SUBSONIQUE DE TURBORÉACTEUR, PAR CAPTEURS DE PRESSION PELLICULAIRES“. Le Journal de Physique Colloques 51, Nr. C2 (Februar 1990): C2–1173—C2–1176. http://dx.doi.org/10.1051/jphyscol:19902275.
Der volle Inhalt der QuelleREDONNET, Stéphane, und Eric MANOHA. „Simulation numérique du bruit aval de soufflante de turboréacteur“. Systèmes aéronautiques et spatiaux, April 2009. http://dx.doi.org/10.51257/a-v1-re125.
Der volle Inhalt der QuelleDissertationen zum Thema "Soufflante de turboréacteur"
Jorajuria, Corentin. „Estimation de l'amortissement des aubages en analyse modale opérationnelle“. Electronic Thesis or Diss., Ecully, Ecole centrale de Lyon, 2024. http://www.theses.fr/2024ECDL0003.
Der volle Inhalt der QuelleEuropean goals to reduce air traffic environmental impacts leads to design new civilian turbojet engines. These new designs can result in more severe aeroelastic risks for turbojet engines. In this regard, understanding and predicting dissipation phenomena is a key industrial challenge. As these phenomena can be very wide and complex, experimental approaches take an important role to understand damping. This thesis focuses on the estimation of damping of fan of civilian turbojet engines. To this end, estimation methods in frequency and time domain have been studied. The estimation issues are addressed thanks to a test rig making possible to measure vibratory responses of rotating full-scale fan in vacuum conditions using piezoelectric excitations. Moreover, subspace identification methods, showing particular advantages for the estimation of modes of rotating fans, have been investigated more specifically. Estimation performances of these techniques have been assessed over numerical models. Then, these techniques have been applied over vibratory measurements of a rotating fan in vacuum conditions. Furthermore, experimental data of fans in operation show that excitations can induce significant transient responses. Accordingly, an experimental study evaluating the effect of unsteady responses over modal characterization has been carried out. This experimental study has been performed thanks to modal tests using excitations with different unsteady rate. Finally, estimation methods showing encouraging results over modal tests of a rotating fan in vacuum conditions have been applied over experimental data obtained in operational conditions
Daroukh, Majd. „Effects of distortion on modern turbofan tonal noise“. Thesis, Toulouse, INPT, 2017. http://www.theses.fr/2017INPT0060/document.
Der volle Inhalt der QuelleFuel consumption and noise reduction trigger the evolution of aircraft engines towards Ultra High Bypass Ratio (UHBR) architectures. Their short air inlet design and the reduction of their interstage length lead to an increased circumferential inhomogeneity of the flow close to the fan. This inhomogeneity, called distortion, may have an impact on the tonal noise radiated from the fan module. Usually, such a noise source is supposed to be dominated by the interaction of fan-blade wakes with Outlet Guide Vanes (OGVs). At transonic tip speeds, the noise generated by the shocks and the steady loading on the blades also appears to be significant. The increased distortion may be responsible for new acoustic sources while interacting with the fan blades and the present work aims at evaluating their contribution. The effects of distortion on the other noise mechanisms are also investigated. The work is based on full-annulus simulations of the Unsteady Reynolds-Averaged Navier-Stokes (URANS) equations. A whole fan module including the inlet duct, the fan and the Inlet and Outlet Guide Vanes (IGVs/OGVs) is studied. The OGV row is typical of current engine architecture with an integrated pylon and two different air inlet ducts are compared in order to isolate the effects of inlet distortion. The first one is axisymmetric and does not produce any distortion while the other one is asymmetric and produces a level of distortion typical of the ones expected in UHBR engines. A description and a quantification of the distortion that is caused by both the potential effect of the OGVs and the inlet asymmetry are proposed. The effects of the distortion on aerodynamics are highlighted with significant modifications of the fanblade wakes, the shocks and the unsteady loading on the blades and on the vanes. Both direct and hybrid acoustic predictions are provided and highlight the contribution of the fan-blade sources to the upstream noise. The downstream noise is still dominated by the OGV sources but it is shown to be significantly impacted by the inlet distortion via the modification of the impinging wakes
Masson, Vianney. „Sound propagation in a possibly lined annular duct with swirling and sheared mean flow : application to fan broadband noise prediction“. Thesis, Lyon, 2018. http://www.theses.fr/2018LYSEC007.
Der volle Inhalt der QuelleThe advent of modern turbofan engines such as UHBR goes along with new issues. Amongst others, the shortening of the inlet and exhaust yield a relatively higher importance of the liners located inside the interstage, where the flow is highly swirling. The present work aims at developing analytical models to assess the effect of the swirl both on the behavior of the interstage liners and on the upstream radiation of the fan-OGV interaction broadband boise. The evolution of small fluctuations in a rigid annular duct containing a swirling and sheared mean flow are studied first. After having introduced the governing equations and the main assumptions, the acoustic analogy of Posson & Peake [122] tailored to an annular duct with swirl and shear is presented. The effect of the swirl on the modal content in a rigid annular duct is highlighted for different types of swirl. In particular the shift of the cut-on thresholds is studied. Then, the modal analysis is extended to a duct with lined walls. A particular attention is paid on the boundary condition. Notably, a correction of the classical Myers boundary condition [101] is proposed to account for the centrifugal effects. An extension of Brambley’s boundary condition [24] is also derived to account for the boundary layer thickness to first order. The effect of both the swirl and the boundary condition on the modal content are studied. Besides, a dispersion relation for the surface waves is derived for the corrected Myers boundary condition. Based on the previous modal analyses, a transmission tool is developed to assess the effect of the swirl on the efficiency of a liner. The method, which relies on the mode-matching approach, is based on the conservation of the total enthalpy and the mass flow at the interfaces between the rigid and the lined sections. Due to the nature of the eigenfunctions, a new projection method based on the Chebyshev polynomial properties is proposed. Thanks to this model, the absorption is assessed for different types of swirl. Finally, a rotor-stator interaction broadband noise prediction model is derived from Posson & Peake’s acoustic analogy [122], to account for the effect of the swirl on the upstream radiated acoustic power. The source term is computed according to Posson et al.’s model [120]. It allows considering a radial variation of the geometry and the statistical properties of the incident turbulence. The model is assessed on the NASA SDT test case and the effect of the swirl is evaluated for several stator geometries and regimes
Reboul, Gabriel. „Modélisation du bruit à large bande de soufflantes de turboréacteurs“. Phd thesis, Ecole Centrale de Lyon, 2010. http://tel.archives-ouvertes.fr/tel-00562647.
Der volle Inhalt der QuelleBen, Nasr Nabil. „Aérodynamique 3-D : application au bruit des soufflantes des turboréacteurs“. Paris 6, 2010. http://www.theses.fr/2010PA066117.
Der volle Inhalt der QuelleDe, Laborderie Jérôme. „Approches analytiques et numériques pour la prédiction du bruit tonal et large bande de soufflantes de turboréacteurs“. Thèse, Université de Sherbrooke, 2013. http://hdl.handle.net/11143/6121.
Der volle Inhalt der QuelleKaya, Tarik. „Étude expérimentale et numérique du fonctionnement d'une soufflante à calage variable en présence d'une distorsion de pression totale en entrée“. Toulouse, ENSAE, 1993. http://www.theses.fr/1993ESAE0023.
Der volle Inhalt der QuelleMabilia, Antoine. „Dynamique non-linéaire d'une soufflante en rotation“. Thesis, Lyon, 2020. http://www.theses.fr/2020LYSEC026.
Der volle Inhalt der QuelleIn an aeronautics industry increasingly concerned by the environmental issues of our time, the mastery of dynamic behavior is of particular interest in terms of compliance with the environmental legislation. Indeed, this allows the structures to be designed as accurately as possible and therefore optimizes the total weight of the turbojet engine, while maintaining an exemplary level of reliability and safety as well as excellent performances. Fully integrated into this theme, the problematics of mistuning and nonlinear dynamics are eminently studied by present academic research, leading to the development of numerical methods that allow these two effects to be taken into account simultaneously. However, the representativity of these numerical methods with respect to the behavior of an actual engine can hardly be evaluated because of the few tests available in the literature. In addition to improving the understanding and prediction of bladed disks vibratory phenomena, this doctoral work has a twofold objective: experimental and numerical. The latter aimed at investigating the representativity of numerical models and methods, particularly developed at the LTDS on the problematics of mistuning and nonlinear dynamics, in comparison with rotating tests on a latest-generation industrial fan made of composite materials. For this purpose, the PHARE#1 test bench, developed over the last few years at the LTDS, allows the testing of bladed disks on a 1:1 scale, rotating in vacuum, while exciting the blades by means of piezoelectric actuators. The numerical methods used to simulate the fan are based on the concept of substructuring associated with a triple modal synthesis, thus allowing the consideration of mistuning within nonlinear problems of industrial size. Two case studies, both experimental and numerical, were conducted and analyzed during this doctoral work. These studies exploit an excitation by means of piezoelectric actuators whose modeling required the development of an electrical degrees of freedom condensation technique in order to benefit from the numerical methods of purely mechanical reduction and resolution. The first study has been carried out on a fan blade embedded in clamping jaws. This application made possible to focus on the nonlinear aspects of contact and friction at the dovetail by comparing the test results and the numerical simulations. The second study was performed on the composite bladed fan rotating in vacuum, thus achieving analyses and comparisons concerning the mistuning of the response and modal shapes coupled with nonlinear effects. The results obtained show a very good representativity of the numerical simulations with respect to the rotating tests in terms of mistuning, especially with respect to the decompositions in diameter components and the spatial distributions of the vibration amplitudes of the blades
Sabah, Muriel. „Etude expérimentale du bruit à large bande d'une grille d'aubes : Application au calcul du bruit des soufflantes“. Ecully, Ecole centrale de Lyon, 2001. http://bibli.ec-lyon.fr/exl-doc/TH_T1878_msabah.pdf.
Der volle Inhalt der QuelleThis study deals with acoustic sources of broadband noise in a linear cascade, aiming at a better understanding of the noise emission in a turbofan engine. The fan, placed at the beginning of turbojet, is nowadays one of the main sources. Noise sources are essentially investigated on a specific experimental set-up, using a model linear cascade made of seven blades, placed at the exit flow of an open anechoïc wind tunnel. Far field acoustic measurements, velocity measurements around the cascade and wall pressure measurements on the blades allow to relate the noise to the unsteady aerodynamics, and so to understand noise mechanisms. The linear cascade is a privileged way of inferring very complicated mechanisms in quite a clear context, avoiding extra noise sources. The objective is not to reproduce the exact flow in a fan, so we neither study the effects of rotation, neither tridimensional flow effects. The goal is to find a transfer function between the wall pressure and the far field. This transfer function must be the same one in a real fan, if the mechanisms are identical. Sources of broadband noise arise either from interaction with upstream turbulence or from blade self-noise associated with turbulent boundary layers convected past the trailing edge. The main goal is to quantify the relative contributions of both sources, and to assess the effect of various parameters. The Reynolds number based on the blade chord is about 106 and the Mach number up to 0. 3, for a blade chord equal to 10cm. For self-noise and turbulence interaction noise, the blade loading effect on noise was studied, by varying the angle of attack. For both of them, the directivity is globally a dipole, with preferred aft-radiation. No blade-to-blade correlation was observed. Besides, self-noise intensity scales with the power 5. 5 to 6 of the flow velocity and turbulence-interaction noise (turbulence rate equal to 5%) scales with the power 5 to 5. 5 of the flow velocity. Apart from the experimental study, an analytical model is validated owing to the measure¬ments. This model is based on a formulation of noise radiated by isolated blade, according to acoustic analogy. The theoretical model, based on Amiet's formulation, shows good agreement with the measurements, for the directivity and the power law of variation with velocity
Chan, Charles. „Outil d’aide à la conception d’un traitement acoustique basé sur des matériaux poreux pour la réduction du bruit de soufflante“. Thesis, Compiègne, 2015. http://www.theses.fr/2015COMP2253.
Der volle Inhalt der QuelleThe constant need to reduce noise emissions from aircraft engine leads to a real demand for developing new acoustic treatments. Conventional liners based on resonatorlike structure continue to be used and provide narrow-band attenuation in spite of an increasing degree of freedom. A possible alternative is the use of porous materials (nonlocally reacting), which offer the possibility of broadening the attenuation spectrum. This report deals with the modelling of an acoustic treatment based on porous materials for aeroengine nacelle inlet. A semi-analytical model is developed for predicting the transmission loss of a treated cylindrical duct containing uniform mean flow. Then, a parametrical study is carried out in order to target the optimal liner characteristics for a given turbofan duct application. Also, experiments have been performed on a small-scale duct and have shown agreement with the simulation. Finally, for a better theoretical unv derstanding of the problem, a preliminary study on the effect of a boundary layer is conducted and shows that its consideration seems to be essential for optimal choice of acoustic lining, espacially at high frequencies