Relevant bibliographies by topics / Multi-Stage Bladed Disks Dynamics

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  2. Dissertations / Theses
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  4. Conference papers

Academic literature on the topic 'Multi-Stage Bladed Disks Dynamics'

Author: Grafiati
Published: 14 March 2023
Last updated: 19 July 2025

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Journal articles on the topic "Multi-Stage Bladed Disks Dynamics"

1

Wagner, L. F., and J. H. Griffin. "Blade Vibration With Nonlinear Tip Constraint: Model Development." Journal of Turbomachinery 112, no. 4 (1990): 778–85. http://dx.doi.org/10.1115/1.2927721.

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Turbine blades having integrally machined tip shrouds, with associated gaps between adjacent shrouds, often exhibit unusual vibratory responses with significant differences between the amplitudes and frequencies of individual blades on the same stage. These differences result from unavoidable variations in the shroud gaps causing, for large enough excitation, nonlinear constraint at the blade tips which varies from blade to blade. This study shows that the blade stresses cannot be adequately represented by the type of single-degree-of-freedom models that are often used for dynamic impact studi
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Laxalde, Denis, Jean-Pierre Lombard, and Fabrice Thouverez. "Dynamics of Multistage Bladed Disks Systems." Journal of Engineering for Gas Turbines and Power 129, no. 4 (2007): 1058–64. http://dx.doi.org/10.1115/1.2747641.

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This paper presents a new and original method for dynamical analysis of multistage cyclic structures such as turbomachinery compressors or turbines. Each stage is modeled cyclically by its elementary sector and the interstage coupling is achieved through a cyclic recombination of the interface degrees of freedom. This method is quite simple to set up; it allows us to handle the finite element models of each stage’s sector directly and, as in classical cyclic symmetry analysis, to study the nodal diameter problems separately. The method is first validated on a simple case study which shows good
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3

Bladh, R., M. P. Castanier, and C. Pierre. "Effects of Multistage Coupling and Disk Flexibility on Mistuned Bladed Disk Dynamics." Journal of Engineering for Gas Turbines and Power 125, no. 1 (2002): 121–30. http://dx.doi.org/10.1115/1.1498267.

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The effects of disk flexibility and multistage coupling on the dynamics of bladed disks with and without blade mistuning are investigated. Both free and forced responses are examined using finite element representations of example single and two-stage rotor models. The reported work demonstrates the importance of proper treatment of interstage (stage-to-stage) boundaries in order to yield adequate capture of disk-blade modal interaction in eigenfrequency veering regions. The modified disk-blade modal interactions resulting from interstage-coupling-induced changes in disk flexibility are found
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4

Laxalde, Denis, and Christophe Pierre. "Modelling and analysis of multi-stage systems of mistuned bladed disks." Computers & Structures 89, no. 3-4 (2011): 316–24. http://dx.doi.org/10.1016/j.compstruc.2010.10.020.

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Repetckii, Oleg, and Van Vinh Nguyen. "DYNAMIC CHARACTERISTICS ANALYSIS OF BLADED DISK TURBOMACHINES BASED ON INTENTIONAL MISTUNING." Perm National Research Polytechnic University Aerospace Engineering Bulletin, no. 62 (2020): 61–70. http://dx.doi.org/10.15593/2224-9982/2020.62.07.

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To increase technical level of energy turbomachine in modern turbomachinery, high reliability and durability of structures are required in the design, manufacture and operation of turbomachine. Any change geometry, mass, material properties of the bladed disk of turbomachine in the design is called mistuning parameters. With a small value of mistuning blades can significantly increase amplitude, displacement or stresses of the blades structures. So, analysis influence of the effect mistuning parameters on the dynamic characteristics in the field of turbomachine is an important and urgent task.
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Grzejszczak-Pączek, Olga, and Adam Kozakiewicz. "FSI Application in the Parametric Analysis of Blade–Disk Connection of Turbojet Engine Compressor." Applied Sciences 13, no. 19 (2023): 10960. http://dx.doi.org/10.3390/app131910960.

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The following paper evaluates the strength properties of the critical area of the turbine rotor stage of a jet engine. This is where the blade is attached to the rotor disk. Important aspects of this issue are characteristic geometrical dimensions and operating factors, e.g., changes in rotor speed. In the article, the strength properties of the rotor stage with a trapezoidal blade–disk connection were analyzed using parametric analysis considering fluid–structure interaction (FSI). Virtual models of the compressor rotor stages were developed, including parametric blade–disk connections and di
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Brinkmann, Katharina, Thomas Hoffmann, Lars Panning-von Scheidt, and Heinrich Stüer. "Transient Resonance Passage of a Mistuned Bladed Disk with and without Underplatform Dampers." International Journal of Turbomachinery, Propulsion and Power 8, no. 4 (2023): 38. http://dx.doi.org/10.3390/ijtpp8040038.

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In this work, the vibration response of an academic free-standing turbine blisk is analyzed in regard to transient resonance passages. Measurement data are recorded using strain gauges and tip timing to evaluate the blades first bending mode both linearly and with two different types of underplatform dampers. These results are validated against steady-state responses and show good agreement with each other. To examine the effects of a transient resonance passage, response functions of each blade are evaluated both with and without the underplatform dampers. It is shown that friction damping is
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Ran, Liaoyuan, Dunant Halim, Chung Ket Thein, and Michael Galea. "Vibration Control of a Multi-Disc Rotor System with Active Lateral Bearings and Disturbance Estimation." INTER-NOISE and NOISE-CON Congress and Conference Proceedings 268, no. 5 (2023): 3935–42. http://dx.doi.org/10.3397/in_2023_0562.

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A rotor system used in a wide range of engineering applications generally consists of a rotor shaft, multiple discs, blades and other essential components, generating a multi-disc rotor arrangement. System uncertainties caused by unbalanced discs and disc mass variation, compounded with external disturbances under different operating conditions, can lead to a variation in rotor-dynamic characteristics with multiple structural resonances, potentially causing an excessive level of rotor lateral vibration. Therefore, to effectively suppress lateral vibration for such a multi-disc rotor system, an
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Belhanafi, Abdelghani, Zied Driss, and Mohamed Salah Abid. "Hydrodynamic Comparative Study on the Pumping Effects of a Square Tank Equipped with Single-Stage and Bi-Stage Impellers." Acta Universitatis Sapientiae, Electrical and Mechanical Engineering 14, no. 1 (2022): 1–12. http://dx.doi.org/10.2478/auseme-2022-0001.

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Abstract A computational fluid dynamics simulation is done for comparative study from the pumping effect on the four surfaces of the stirred tank. The flow field generated by one-stage and bi-stage six-bladed Rushton turbine in the unbaffled square tank was studied. The Reynolds-averaged Navier-Stokes equation with steady-state multi-reference frame approach (MRF) is used to simulate hydrodynamic flow in the tank. The turbulent viscosity, the turbulent kinetic energy and mean velocity distributions obtained in vertical and horizontal plans are analyzed and discussed. We can deduce that the add
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Shengxi, Jia, Zheng Longxi, Jingjing Huang, and Qing Mei. "Dynamic Characteristics Analysis and Optimization Design of a Simulated Power Turbine Rotor Based on Finite Element Method." International Journal of Turbo & Jet-Engines 37, no. 1 (2020): 31–39. http://dx.doi.org/10.1515/tjj-2017-0006.

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AbstractThe vibration optimum design for a simulated power turbine rotor without blades on the disk by using an optimization method based on the finite element method is described in this paper. The installation position of the two-stage turbine disks is chosen as design variables under the constraints of feasible regions for the critical speeds of the rotor. The objective functions are to minimize the transient response of the acceleration at the bearings and the amplitude of the disks. Predictions of the dynamic characteristics of the rotor are obtained by using ANSYS code. The optimization
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Dissertations / Theses on the topic "Multi-Stage Bladed Disks Dynamics"

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BATTIATO, GIUSEPPE. "Vibrations prediction and measurement of multi-stage bladed disks with non linear behavior due to friction contacts." Doctoral thesis, Politecnico di Torino, 2017. http://hdl.handle.net/11583/2680969.

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The architecture of current aircraft turbofan engines consists of multi-stage assemblies resulting from the coupling of bladed disks by means of bolted flange joints. The efficiency of such systems in real working condition is strictly related to the dynamic properties of blades and disks constituting them. According to the current design practices, blades and disks are designed so that their weights are reduced and their slenderness increased. Therefore, latest generation turbofan engine thus result much more sensible to mechanical vibrations that may cause failure by high cycle fatigue pheno
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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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Segui, Vasquez Bartolomé. "Modélisation dynamique des systèmes disque aubes multi-étages : Effets des incertitudes." Phd thesis, INSA de Lyon, 2013. http://tel.archives-ouvertes.fr/tel-00961270.

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Les conceptions récentes de turbomachines ont tendance à évoluer vers des liaisons entre étages de plus en plus souples et des niveaux d'amortissement faibles, donnant lieu à des configurations où les modes sont susceptibles de présenter des niveaux de couplages inter-étages forts. En général, les ensembles disques aubes multi-étagés n'ont aucune propriété de symétrie cyclique d'ensemble et l'analyse doit porter sur un modèle de la structure complète donnant lieu à des calculs très coûteux. Pour palier ce problème, une méthode récente appelée symétrie cyclique multi-étages peut être utilisée p
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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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Book chapters on the topic "Multi-Stage Bladed Disks Dynamics"

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Berger, Ricarda, and Raimund Rolfes. "Dynamical Behaviour and Strength of Structural Elements with Regeneration Induced Imperfections and Residual Stresses." In Regeneration of Complex Capital Goods. Springer International Publishing, 2024. http://dx.doi.org/10.1007/978-3-031-51395-4_10.

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AbstractRepair techniques allow to refurbish blades of jet engines and extend the service life of engine components. However, the mechanical properties of the repaired blades commonly differ from those of the nominal blades. The changes in vibration behaviour and stress distribution resulting from the repair processes could significantly impair the structural integrity of blades. This work addresses this evaluation of repair-specific influences on the structural integrity of blades of blade-integrated disks (blisks). Numerical methods are employed to model and analyse the structural changes of different repair designs. Using Finite Element (FE) simulations, the influences of different repair techniques and designs are systematically evaluated and compared. To further improve the maintenance procedures of blisks, a computational scheme is developed, which features the optimization of repair designs according to the inspected damage of the blade. Since the corresponding optimization tasks involve multiple conflicting objectives, multi-objective optimization is carried out to identify Pareto-optimal repair designs.
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Conference papers on the topic "Multi-Stage Bladed Disks Dynamics"

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Duraisamy, Karthik, and Anand Singh. "Multi Fidelity Aerodynamic Design of Ducted Microscale Rotor Systems." In Vertical Flight Society 70th Annual Forum & Technology Display. The Vertical Flight Society, 2014. http://dx.doi.org/10.4050/f-0070-2014-9428.

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Computational fluid dynamic models of varying fidelity are used in the analysis and design of a ducted micro scale rotor system. A three dimensional Reynolds Averaged Navier-Stokes (RANS) solver is employed as the high fidelity model, an axisymmetric RANS approach with a blade element representation of the rotor is used as the low fidelity model and an axisymmetric inviscid actuator disk model is used to relate the present work to analytical theories. A ducted rotor system (at a tip Reynolds number of 50000) is used for validation purposes and to serve as a baseline for design improvements und
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2

Laxalde, Denis, Jean-Pierre Lombard, and Fabrice Thouverez. "Dynamics of Multi-Stage Bladed Disks Systems." In ASME Turbo Expo 2007: Power for Land, Sea, and Air. ASMEDC, 2007. http://dx.doi.org/10.1115/gt2007-27083.

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This paper presents a new and original method for dynamical analysis of multi-stage cyclic structures such as turbomachinery compressors or turbines. Each stage is modeled cyclically by its elementary sector and the inter-stage coupling is achieved through a cyclic recombination of the interface degrees of freedom. This method is quite simple to set-up; it allows to handle the finite element models of each stage’s sector directly and, as in classical cyclic symmetry analysis, to study the nodal diameter problems separately. The method is first validated on a simple case study which shows good
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3

Bladh, Ronnie, Matthew P. Castanier, and Christophe Pierre. "Effects of Multi-Stage Coupling and Disk Flexibility on Mistuned Bladed Disk Dynamics." In ASME Turbo Expo 2001: Power for Land, Sea, and Air. American Society of Mechanical Engineers, 2001. http://dx.doi.org/10.1115/2001-gt-0277.

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The effects of disk flexibility and multi-stage coupling on the dynamics of bladed disks with and without blade mistuning are investigated. Both free and forced responses are examined using finite element representations of example single- and two-stage rotor models. The reported work demonstrates the importance of proper treatment of interstage (stage-to-stage) boundaries in order to yield adequate capture of disk-blade modal interaction in eigenfrequency veering regions. The modified disk-blade modal interactions resulting from interstage-coupling-induced changes in disk flexibility are foun
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4

Laxalde, Denis, and Fabrice Thouverez. "Non-Linear Vibrations of Multi-Stage Bladed Disks Systems With Friction Ring Dampers." In ASME 2007 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2007. http://dx.doi.org/10.1115/detc2007-34473.

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In this paper, we study the non-linear dynamics of a multi-stage system of turbomachinery bladed disks with friction dampers. We focus on the quasi-periodic forced response of this system under multi-frequency rotating excitations. The system’s equations of the motion are expressed in the multi-frequency domain using a multi-frequency harmonic balance method in combination a multi-stage cyclic symmetry reduction. A Dynamic Lagrangian formulation in alternating frequency/time domains is also used for the calculation of the contact and friction forces. In applications we consider a system of two
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D'Souza, Kiran, Akira Saito, and Bogdan Epureanu. "Reduced Order Modeling for Nonlinear Vibration Analysis of Mistuned Multi-Stage Bladed Disks with a Cracked Blade." In 52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-2065.

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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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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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Yu, Hongbiao, and K. W. Wang. "Vibration Suppression of Mistuned Coupled-Blade-Disk Systems Using Piezoelectric Circuitry Network." In ASME 2007 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2007. http://dx.doi.org/10.1115/detc2007-34443.

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In this research, piezoelectric networking is investigated as an effective means for vibration suppression of mistuned bladed disk systems. Due to mistuning (i.e., imperfections in blade properties), bladed disks in turbo-machinery often suffer from vibration localization. In such cases, the vibration energy is confined to a small number of blades and forced response can be drastically increased when the structure is under engine order force excitation. To suppress the excessive vibration caused by localization, a piezoelectric networking concept has been proposed and analyzed for a multi-blad
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Rzadkowski, Romuald, and Artur Maurin. "Multi-Stage Coupled Forced Response of Aircraft Engine Compressor and Turbine Bladed Discs." In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-57643.

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Considered here is the effect of multistage coupling on the dynamics of an aircraft engine rotor with eight mistuned bladed discs on a drum-disc shaft during foreign object ingestion (FOI). In the dynamic model, each disc had a different number of rotor blades. Free and forced vibrations were examined using finite element models of single rotating blades, bladed discs and an entire rotor with bladed discs. Calculations of the mode shapes of flexible mistuned bladed disc-shaft assemblies took into account simultaneous excitations of the first and second stages of the compressor and the turbine
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Srinivas, Siva, Hardik Roy, and Esakki Muthu Shanmugam. "Study of the Effect of Multi-Stage Cyclic Symmetric Modeling on the Natural Frequencies of Bladed Disks of an Aero Engine Rotor System." In ASME 2015 Gas Turbine India Conference. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gtindia2015-1297.

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Majority of the failures in Gas turbine Blades are caused by High Cycle Fatigue induced by the vibratory stresses in the rotor blades. The first step in blade design is the prevention of coincidence of natural frequencies of the blades with the frequencies of the fluctuating Gas loads. The forcing frequency is a function of number of upstream and downstream stator blades, and rotational speed. In gas turbines with multiple stages, modal analysis of bladed-disks is individually performed i.e. stage by stage. As the structure is rotationally periodic, cyclic symmetric boundary conditions can be
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Firrone, Christian M., Giuseppe Battiato, and Bogdan I. Epureanu. "Modelling the Microslip in the Flange Joint and its Effect on the Dynamics of a Multi-Stage Bladed Disk Assembly." In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-57998.

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The complex architecture of aircraft engines requires demanding computational efforts to take into account the dynamic coupling of the many components constituting the whole assembly. For this reason numerically efficient Reduced Order Models (ROM) and techniques have been developed with the aim of reproducing the global dynamics of the system being computationally fast at the same time. In particular, ROMs have been presented to perform the modal analysis and the calculation of the forced response of rotating components like turbine bladed disks multi-stage assembly. In order to study the eff
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