Relevant bibliographies by topics / Bladed Disks Dynamic

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers

Academic literature on the topic 'Bladed Disks Dynamic'

Author: Grafiati
Published: 14 March 2023

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Journal articles on the topic "Bladed Disks Dynamic"

1

Zhao, Zhi Bin, Er Ming He, and Hong Jian Wang. "Experimental Investigation on Natural Characteristics and Forced Response of Bladed Disks." Applied Mechanics and Materials 105-107 (September 2011): 34–37. http://dx.doi.org/10.4028/www.scientific.net/amm.105-107.34.

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The results of an experimental investigations on the natural characteristics of tuned bladed disk and forced dynamic responses of mistuned bladed disks are reported. Three experimental bladed disks are discussed: a tuned specimen of periodic symmetry with 12-blades which are nominally identical, and two mistuned specimens, which feature small blade-to-blade variations by adding slight blocks to blade tips. All the specimens are subject to travelling wave excitation produced by piezo-electric actuators sticking on the root of blades. The primary objective of this experiment is to observe the na
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Judge, J., C. Pierre, and O. Mehmed. "Experimental Investigation of Mode Localization and Forced Response Amplitude Magnification for a Mistuned Bladed Disk." Journal of Engineering for Gas Turbines and Power 123, no. 4 (2000): 940–50. http://dx.doi.org/10.1115/1.1377872.

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The results of an experimental investigation on the effects of random blade mistuning on the forced dynamic response of bladed disks are reported. The primary aim of the experiment is to gain understanding of the phenomena of mode localization and forced response blade amplitude magnification in bladed disks. A stationary, nominally periodic, 12-bladed disk with simple geometry is subjected to a traveling-wave out-of-plane “engine order” excitation delivered via phase-shifted control signals sent to piezoelectric actuators mounted on the blades. The bladed disk is then mistuned by the addition
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Bladh, R., M. P. Castanier, and C. Pierre. "Component-Mode-Based Reduced Order Modeling Techniques for Mistuned Bladed Disks—Part I: Theoretical Models." Journal of Engineering for Gas Turbines and Power 123, no. 1 (2000): 89–99. http://dx.doi.org/10.1115/1.1338947.

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Component mode synthesis (CMS) techniques are widely used for dynamic analyses of complex structures. Significant computational savings can be achieved by using CMS, since a modal analysis is performed on each component structure (substructure). Mistuned bladed disks are a class of structures for which CMS is well suited. In the context of blade mistuning, it is convenient to view the blades as individual components, while the entire disk may be treated as a single component. Individual blade mistuning may then be incorporated into the CMS model in a straightforward manner. In this paper, the
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Carassale, Luigi, and Elena Rizzetto. "Experimental Investigation on a Bladed Disk with Traveling Wave Excitation." Sensors 21, no. 12 (2021): 3966. http://dx.doi.org/10.3390/s21123966.

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Bladed disks are key components of turbomachines and their dynamic behavior is strongly conditioned by their small accidental lack of symmetry referred to as blade mistuning. The experimental identification of mistuned disks is complicated due to several reasons related both to measurement and data processing issues. This paper describes the realization of a test rig designed to investigate the behavior of mistuned disks and develop or validate data processing techniques for system identification. To simplify experiments, using the opposite than in the real situation, the disk is fixed, while
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Gao, Shimin, Yanrong Wang, Zhiwei Sun, and Siyuan Chen. "A Prediction Method with Altering Equivalent Stiffness for Damping Evaluation of Shrouded Bladed Disk Dynamic Systems." Symmetry 13, no. 3 (2021): 413. http://dx.doi.org/10.3390/sym13030413.

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In turbomachinery bladed disks are typical cyclic symmetric structures where high-cycle fatigue of the blades can easily occur. Increasing the shroud structure is an effective blade vibration reduction method using the dry friction of the shroud contact surface to dissipate vibration energy. During one vibration cycle of the blade, the contact surface of the shroud may have one or several states of stick, slip, and separation due to the different amplitude of blade, which affects not only the damping, but also the stiffness of the system. This paper proposes a method to analyze the damping cha
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Mignolet, M. P., A. J. Rivas-Guerra, and J. P. Delor. "Identification of Mistuning Characteristics of Bladed Disks From Free Response Data—Part I." Journal of Engineering for Gas Turbines and Power 123, no. 2 (1999): 395–403. http://dx.doi.org/10.1115/1.1338949.

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The focus of the present two-part investigation is on the estimation of the dynamic properties, i.e., masses, stiffnesses, natural frequencies, mode shapes and their statistical distributions, of turbomachine blades to be used in the accurate prediction of the forced response of mistuned bladed disks. As input to this process, it is assumed that the lowest natural frequencies of the blades alone have been experimentally measured, for example, in a broach block test. Since the number of measurements is always less than the number of unknowns, this problem is indeterminate in nature. In this fir
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Sommariva, Alessandro, and Stefano Zucca. "A Comparison between Two Reduction Strategies for Shrouded Bladed Disks." Applied Sciences 8, no. 10 (2018): 1736. http://dx.doi.org/10.3390/app8101736.

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Shrouded bladed disks exhibit a nonlinear dynamic behavior due to the contact interfaces at shrouds between neighboring blades. As a result, reduced order models (ROMs) are mandatory to compute the response levels during the design phase for high cycle fatigue (HCF) life assessment. In this paper, two reduction strategies for shrouded bladed disk reduction are presented. Both approaches rely on: (i) the cyclic symmetry of the linear bladed disk with open shrouds to perform only single sector calculations, (ii) the Craig–Bampton (CB) method to reduce the number of physical degrees of freedom (d
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Moraga, Greco, Mònica Egusquiza, David Valentín, Carme Valero, and Alexandre Presas. "Analysis of the Mode Shapes of Kaplan Runners." Applied Sciences 12, no. 13 (2022): 6708. http://dx.doi.org/10.3390/app12136708.

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To prevent lifetime shortening and premature failure in turbine runners, it is of paramount importance to analyse and understand its dynamic response and determine the factors that affect it. In this paper, the dynamic response of a Kaplan runner is analysed in air by numerical and experimental methods. First, to start the analysis of Kaplan runner mode shapes, its geometry is simplified and modelled as a bladed disk. Bladed disks with different blade numbers are investigated, by numerical simulation, in order to understand the influence of this parameter on its modal characteristics. Then, mo
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Flowers, G. T., and Fang Sheng Wu. "A Study of the Influence of Bearing Clearance on Lateral Coupled Shaft/Disk Rotordynamics." Journal of Engineering for Gas Turbines and Power 115, no. 2 (1993): 279–86. http://dx.doi.org/10.1115/1.2906706.

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This study examines the influence of bearing clearance on the dynamic behavior of a rotating, flexible disk/shaft system. Most previous work in nonlinear rotordynamics has tended to concentrate separately on shaft vibration or on bladed disk vibration, neglecting the coupling dynamics between them. The current work examines the important rotordynamic behavior of coupled disk/shaft dynamics. A simplified nonlinear model is developed for lateral vibration of a rotor system with a bearing clearance nonlinearity. The steady-state dynamic behavior of this system is explored using numerical simulati
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Petrov, E. P., and D. J. Ewins. "Advanced Modeling of Underplatform Friction Dampers for Analysis of Bladed Disk Vibration." Journal of Turbomachinery 129, no. 1 (2006): 143–50. http://dx.doi.org/10.1115/1.2372775.

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Advanced structural dynamic models for both wedge and split underplatform dampers have been developed. The new damper models take into account inertia forces and the effects of normal load variation on stick-slip transitions at the contact interfaces. The damper models are formulated for the general case of multiharmonic forced response analysis. An approach for using the new damper models in the dynamic analysis of large-scale finite element models of bladed disks is proposed and realized. Numerical investigations of bladed disks are performed to demonstrate the capabilities of the new models
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Dissertations / Theses on the topic "Bladed Disks Dynamic"

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Bah, Mamadou Tahirou. "Reduced order modelling for efficient prediction of the dynamics of mistuned bladed disks." Thesis, University of Southampton, 2002. https://eprints.soton.ac.uk/45931/.

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The unavoidable existence of small differences between nominally identical sectors of bladed disks, called mistuning, can have an important impact on the dynamic behaviour of these structures. In particular, this has the potential to lead to responses qualitatively different from that of an ideal cyclic, tuned structure and, in turn, to significantly shorter life spans. Study of mistuning as a random phenomenon requires statistical analysis of a large number of mistuning patterns. This computational task is expensive especially when high-fidelity finite element models are used. This research i
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Fang, Chih. "A reduced-order meshless energy (ROME) model for the elastodynamics of mistuned bladed disks." Diss., Georgia Institute of Technology, 2002. http://hdl.handle.net/1853/12457.

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Yumer, Mehmet Ersin. "On The Non-linear Vibration And Mistuning Identification Of Bladed Disks." Master's thesis, METU, 2010. http://etd.lib.metu.edu.tr/upload/3/12611498/index.pdf.

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Forced response analysis of bladed disk assemblies plays a vital role in rotor blade design and has been drawing a great deal of attention both from research community and engine industry for more than half a century. However because of the phenomenon called &lsquo<br>mistuning&rsquo<br>, which destroys the cyclic symmetry of a rotor, there have been several difficulties related to forced response analysis ever since, two of which are addressed in this thesis: efficient non-linear forced response analysis of mistuned bladed disks and mistuning identification. On the nonlinear analysis side, a
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Sternchüss, Arnaud. "Multi-level parametric reduced models of rotating bladed disk assemblies." Phd thesis, Ecole Centrale Paris, 2009. http://tel.archives-ouvertes.fr/tel-00366252.

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Les disques aubagés, que l'on trouve dans les turbomachines, sont des structures complexes dont le comportement vibratoire est généralement déterminé par l'exploitation de conditions de symétrie dans leur configuration nominale. Cette symétrie disparaît lorsque l'on assemble plusieurs de ces disques pour former un rotor ou que l'on introduit une variabilité spatiale des paramètres mécaniques (on parle de désaccordage intentionnel ou non). Le raffinement des maillages, nécessaire à une évaluation correcte de la répartition des contraintes, conduirait à des modèles de rotor complet de taille pro
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Picou, Anthony. "Robust analysis under uncertainties of bladed disk vibration with geometrical nonlinearities and detuning." Thesis, Paris Est, 2019. http://www.theses.fr/2019PESC2038.

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Le désaccordage intentionnel, plus communément appelé detuning, a été identifié comme une possible technonologie pour réduire la sensibilité du comportement dynamique de roues aubagées soumises au désaccordage involontaire, aussi appelé mistuning, causé par les dispersions matérielle d'une aube à une autre engendrées lors du processus de fabrication et par la variabilité des propriétés mécaniques des matériaux. Le désaccordage intentionnel est mis en place par l'introduction de motifs à partir desquels différents types de secteurs générateurs, ayant des propriétés géométriques et matérielles d
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Shankare, Gowda Vrishank Raghav. "Radial flow effects on a retreating rotor blade." Diss., Georgia Institute of Technology, 2014. http://hdl.handle.net/1853/53403.

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This work studies the effects of radial flow on the aerodynamic phenomena occurring on a retreating blade with a focus on dynamic stall and reverse flow as applied to both a helicopter rotor in forward flight and a wind turbine operating at a yaw angle. While great progress has been made in understanding the phenomenon of two-dimensional dynamic stall, the effect of rotation on the dynamic stall event is not well understood. Experiments were conducted on a rigid two bladed teetering rotor at high advance ratios in a low speed wind tunnel. Particle image velocimetry (PIV) measurements were used
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Dumartineix, Cécile. "Modélisation et étude de la dynamique complexe d'un système bi-rotor aubagé couplé." Thesis, Lyon, 2019. http://www.theses.fr/2019LYSEC049.

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L'optimisation des turboréacteurs nécessite une excellente maîtrise des phénomènes vibratoires de la structure complète et notamment des interactions entre les différents organes constitutifs du moteur. Dans le cas d'une ligne d'arbre, le couplage entre dynamique d'ensemble et dynamique d'aubages modifie le comportement des roues aubagées, généralement dimensionnées individuellement. La prise en compte de ce phénomène fait intervenir des modèles de grandes tailles, justifiant la nécessité de développer des outils numériques spécifiques intégrant une stratégie de résolution peu coûteuse. Ces éc
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Salles, Loïc. "Etude de l'usure par fretting sous chargements dynamiques dans les interfaces frottantes : application aux pieds d'aubes de turbomachines." Phd thesis, Ecole Centrale de Lyon, 2010. http://tel.archives-ouvertes.fr/tel-00600613.

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Les parties tournantes des turbomachines aéronautiques sont composées d'une succession de roues aubagées qui permettent le transfert de l'énergie entre l'air et le rotor. Ces roues aubagées constituent des pièces particulièrement sensibles car elles doivent répondre en termes de dimensionnement à des impératifs de performances aérodynamiques, d'aéroacoustique et de tenue mécanique à la rotation,à la température et à la charge aérodynamique. Le contact avec frottement existant au niveau des attaches aube-disque joue un rôle important sur les niveaux vibratoires.Ce travail porte sur l'étude de l
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Óttarsson, Gísli. "Dynamic modeling and vibration analysis of mistuned bladed disks." Phd thesis, 1994. http://tel.archives-ouvertes.fr/tel-00598068.

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One of the most important problems that plague turbomachinery rotors is the existence of rogue blades -- lone blades that exhibit unexpected fatigue failure. It has been recognized that rotor mistuning might be the cause of rogue blades through a phenomenoncalled normal mode localization, whereby vibration energy is confined to a few blades of the assembly. The goals of this dissertation are (1) to achieve a thorough understanding of the fundamental mechanisms governing mistuning effects, (2) the development of mathematical models of turbomachinery rotors suitable for mistuning analysis, and (
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Cheng, Wen-Yuan, and 鄭文源. "Dynamic Modeling of Bladed-Disks Using Pseudo Mode Shape Method." Thesis, 2007. http://ndltd.ncl.edu.tw/handle/71562129059071766246.

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碩士<br>元智大學<br>機械工程學系<br>95<br>Vibration coupling occurs between bladed disks and shafts in high-speed rotors of large steam turbine-generators. Therefore, the effects of bladed disks on the shafts can not be neglected. If solid elements are used in the finite element modeling of multiple-bladed-disk rotors, problems of huge amount of elements and time consuming in computation often make simulation and analysis impractical. Model reduction is necessary to reduce the size of the matrices of substructures for computation. On the other hand, both limited test points in setting the measurement
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Books on the topic "Bladed Disks Dynamic"

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V, Nagpal, Chamis C. C, and United States. National Aeronautics and Space Administration., eds. Probabilistic analysis of bladed turbine disks and the effect of mistuning. National Aeronautics and Space Administration, 1990.

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Center, Lewis Research, ed. Parallel processing for nonlinear dynamics simulations of structures including rotating bladed-disk assemblies: Report to NASA Lewis Research Center. School of Civil and Environmental Engineering and Program of Computer Graphics, Cornell University, 1993.

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J, Maffeo Robert, Schwartz S, and United States. National Aeronautics and Space Administration., eds. Engine structures analysis software: Component specific modeling (COSMO). National Aeronautics and Space Administration, 1994.

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Book chapters on the topic "Bladed Disks Dynamic"

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Kaneko, Yasutomo, Kazushi Mori, and Hiroharu Ooyama. "Vibration Response Analysis of Mistuned Bladed Disk Consisting of Directionally Solidified Blade." In Proceedings of the 9th IFToMM International Conference on Rotor Dynamics. Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-06590-8_9.

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Carassale, Luigi, Mirko Maurici, and Laura Traversone. "Reduced-Order Modeling of Turbine Bladed Discs by 1D Elements." In Special Topics in Structural Dynamics, Volume 6. Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-15048-2_13.

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Carassale, Luigi, Andrea Bessone, and Andrea Cavicchi. "Interface Reduction in Component Mode Synthesis of Bladed Disks by Orthogonal-Polynomial Series." In Dynamics of Coupled Structures, Volume 4. Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-74654-8_17.

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Ewins, D. J., and Y. J. Chan. "Vibration of Rotating Bladed Discs: Mistuning, Coriolis, and Robust Design." In IUTAM Symposium on Emerging Trends in Rotor Dynamics. Springer Netherlands, 2010. http://dx.doi.org/10.1007/978-94-007-0020-8_15.

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Rzadkowski, Romuald, Artur Maurin, and Ryszard Szczepanik. "Forced Vibration of Eight Mistuned Bladed Discs on a Solid Shaft—Excitation of the Second Compressor Bladed Disc." In Proceedings of the 9th IFToMM International Conference on Rotor Dynamics. Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-06590-8_8.

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Ma, Hui, Zhiyuan Wu, Xingyu Tai, Chaofeng Li, and Bangchun Wen. "Nonlinear Behavior Analysis Caused by Blade Tip Rubbing in a Rotor-Disk-Blade System." In Proceedings of the 9th IFToMM International Conference on Rotor Dynamics. Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-06590-8_15.

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Pešek, Luděk, Pavel Šnábl, Petr Šulc, Ladislav Půst, and Vítězslav Bula. "3D FE modelling of non-linear dynamics of bladed model disk with dry-friction contacts in tie-bosses." In Advances in Mechanism and Machine Science. Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-20131-9_338.

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Nikolaev, Evgeny, and Maria Nikolaeva. "Discrete Vortex Cylinders Method for Calculating the Helicopter Rotor-Induced Velocity." In Vortex Dynamics Theories and Applications. IntechOpen, 2020. http://dx.doi.org/10.5772/intechopen.93186.

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A new vortex model of a helicopter rotor with an infinite number of blades is proposed, based on Shaidakov’s linear disk theory for calculating inductive speeds at any point in space in the helicopter area. It is proposed to consider the helicopter rotor and the behind vortex column as a system of discrete vortex cylinders. This allows building a matrix of the influence of the vortex system under consideration on any set of points, for example, the calculated points on the rotor itself, on the tail rotor, etc. The model allows calculating inductive velocities at any point near the helicopter using matrix multiplication operation. It is shown that the classical results for the momentum theory remain constant even in the discrete simulation of the helicopter rotor vortex system. The structure of the air flow behind the rotor and the simulation results obtained by the proposed method is compared with the structure of the tip vortices and the results of the blade vortex theory. In addition, the experimental data were compared with the simulation results to verify the correctness of the model under real operating conditions by the helicopter trimming.
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Maria, Christian, and Stefano Zucc. "Modelling Friction Contacts in Structural Dynamics and its Application to Turbine Bladed Disks." In Numerical Analysis - Theory and Application. InTech, 2011. http://dx.doi.org/10.5772/25128.

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Conference papers on the topic "Bladed Disks Dynamic"

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Kruse, Marlin J., and Christophe Pierre. "An Experimental Investigation of Vibration Localization in Bladed Disks: Part II — Forced Response." In ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1997. http://dx.doi.org/10.1115/97-gt-502.

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The results of an experimental investigation on the effects of random blade mistuning on the forced dynamic response of bladed disks are reported. Two experimental specimens are considered: a nominally periodic twelve-bladed disk with equal blade lengths, and the corresponding mistuned bladed disk, which features slightly different blades of random lengths. Both specimens are subject to traveling-wave excitations delivered by piezo-electric actuators. The primary aim of the experiment is to demonstrate the occurrence of an increase in forced response blade amplitudes due to mistuning, and to v
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Salles, Loi¨c, Alexander M. Gouskov, Laurent Blanc, Fabrice Thouverez, and Pierrick Jean. "Dynamic Analysis of Fretting-Wear in Joint Interface by a Multiscale Harmonic Balance Method Coupled With Explicit or Implicit Integration Schemes." In ASME Turbo Expo 2010: Power for Land, Sea, and Air. ASMEDC, 2010. http://dx.doi.org/10.1115/gt2010-23264.

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Assembled bladed disks have many contact interfaces (blade-disk joint, blade shrouds, friction damper, etc). Because of relative displacements at these interfaces, fretting-wear can occur, which shortens the life expectancy of the structure. Moreover, vibrations that occur in bladed-disks can increase this fretting-wear phenomenon. Two previous papers in Turboexpo have introduced a numerical method based on the Dynamical Lagrangian Frequency Time algorithm (DLFT) to calculate worn geometry, especially wear of bladed-disks’ dovetail roots. Numerical investigations have illustrated the performan
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Kruse, Marlin J., and Christophe Pierre. "An Experimental Investigation of Vibration Localization in Bladed Disks: Part I — Free Response." In ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1997. http://dx.doi.org/10.1115/97-gt-501.

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The results of an experimental investigation of the effects of random blade mistuning on the free dynamic response of bladed disks are reported. Two experimental specimens are considered: a nominally periodic twelve-bladed disk with equal blade lengths, and the corresponding mistuned bladed disk, which features slightly different, random blade lengths. In the experiment, both the spatially extended modes of the tuned system and the localized modes of the mistuned system are identified. Particular emphasis is placed on the transition to localized mode shapes as the modal density in various freq
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Tong, Jing, Chaoping Zang, and E. P. Petrov. "Accurate Interpolation of the Dependency of Modal Properties on the Rotation Speed for the Transient Response Analysis of Bladed Disks." In ASME Turbo Expo 2021: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2021. http://dx.doi.org/10.1115/gt2021-58982.

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Abstract During fast gas-turbine engine acceleration and deceleration the transient vibration effects in bladed disk vibration become significant and the transient response has to be calculated. In this paper an effective method is developed for efficient calculations of the transient vibration response for mistuned bladed disks under varying rotation speeds. The method uses the large-scale finite element modelling of the bladed disks allowing the accurate description of the dynamic properties of the mistuned bladed disks. The effects of the varying rotation speed on the natural frequencies an
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Beck, Joseph A., Alex A. Kaszynski, Jeffrey M. Brown, Daniel L. Gillaugh, and Onome E. Scott-Emuakpor. "Selection of Dynamic Testing Measurement Locations for Integrally Bladed Disks." In ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/gt2018-76791.

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The selection of sensor locations during dynamic testing of integrally bladed disks (Blisks) is discussed for measuring experimental mode shapes. As-manufactured geometries of the experimental Blisk are obtained in point-cloud form via a structured light optical measurement system. The nominal finite element mesh of the Blisk is then “morphed” to the average sector of as-measured, point-cloud geometry through a mesh metamorphosis algorithm. A ray-tracing algorithm is developed for selecting observable degrees of freedom (DOFs) of the morphed mesh to an overhead laser scanning vibrometer. This
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Hohl, Andreas, Benedikt Kriegesmann, Jo¨rg Wallaschek, and Lars Panning. "The Influence of Blade Properties on the Forced Response of Mistuned Bladed Disks." In ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition. ASMEDC, 2011. http://dx.doi.org/10.1115/gt2011-46826.

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In turbomachinery applications bladed disks are subjected to high dynamic loads due to fluctuating gas forces. Dynamic excitation can result in high vibration amplitudes which can lead to high cycle fatigue (HCF) failures. Herein, the blades are almost identical but differ due to wear or small manufacturing tolerances. Especially, after regeneration and repair procedures the properties of the blades can differ with a high variance. These deviations of the blade properties can lead to a localization of the vibrational energy in single blades and even higher risk of HCF. A recently developed sub
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Judge, John, Christophe Pierre, and Oral Mehmed. "Experimental Investigation of Mode Localization and Forced Response Amplitude Magnification for a Mistuned Bladed Disk." 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-0358.

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The results of an experimental investigation on the effects of random blade mistuning on the forced dynamic response of bladed disks are reported. The primary aim of the experiment is to gain understanding of the phenomena of mode localization and forced response blade amplitude magnification in bladed disks. A stationary, nominally periodic, twelve-bladed disk with simple geometry is subjected to a traveling-wave, out-of-plane, “engine order” excitation delivered via phase-shifted control signals sent to piezo-electric actuators mounted on the blades. The bladed disk is then mistuned by the a
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Mignolet, Marc P., and Alejandro Rivas-Guerra. "Identification of Mistuning Characteristics of Bladed Disks From Free Response Data." In ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/98-gt-583.

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The focus of the present investigation is on the estimation of the dynamic properties, i.e. masses, stiffnesses, natural frequencies, mode shapes and their statistical distributions, of turbomachine blades to be used in the accurate prediction of the forced response of mistuned bladed disks. As input to this process, it is assumed that the lowest natural frequencies of the blades alone have been experimentally measured, for example in a broach block test. Since the number of measurements is always less than the number of unknowns, this problem is indeterminate in nature. Two distinct approache
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Salles, Loi¨c, Laurent Blanc, Fabrice Thouverez, Aleksander M. Gouskov, and Pierrick Jean. "Dynamic Analysis of a Bladed Disk With Friction and Fretting-Wear in Blade Attachments." In ASME Turbo Expo 2009: Power for Land, Sea, and Air. ASMEDC, 2009. http://dx.doi.org/10.1115/gt2009-60151.

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Assembled bladed disks have many contact interfaces (blade-disk joint, blade shrouds, friction dampers...). Because of relative displacements at these interfaces, fretting-wear occurs, which affects negatively the lifetime of the structure. Methods exist to predict fretting-wear in quasi-static analysis. However they don’t predict all the phenomena observed in blade attachments on real industrial plants. This paper studies the assumption of a responsibility of dynamics for fretting-wear damage. A numerical treatment of fretting-wear under vibratory loading is proposed. The method is based on t
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10

Boulton, Luis A., and Euro Casanova. "Reduced Order Model for a Two Stage Gas Turbine Including Mistuned Bladed Disks and Shaft Interaction." In ASME Turbo Expo 2009: Power for Land, Sea, and Air. ASMEDC, 2009. http://dx.doi.org/10.1115/gt2009-59335.

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Abstract:
A number of previous works have suggested that in some cases the interaction between shaft and bladed disk modes could significantly modify the dynamics of the whole assembly i.e. the bladed disks mounted on a flexible shaft. This paper presents the application of a previously published reduced-order modeling technique to the dynamical modeling of a real two stage gas turbine, including the bladed disks and the shaft. In the resulting reduce order model, mistuning is included in the bladed disk models and the shaft is modeled using beam finite elements according to the classical rotordynamic a
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