Relevant bibliographies by topics / Radial-axial oscillations of single-disk rotor

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  1. Journal articles
  2. Dissertations / Theses
  3. Conference papers

Academic literature on the topic 'Radial-axial oscillations of single-disk rotor'

Author: Grafiati
Published: 28 May 2022
Last updated: 31 July 2025

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Journal articles on the topic "Radial-axial oscillations of single-disk rotor"

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Hao, Long, Dongjiang Han, Wei Zhao, Qingjun Zhao, and Jinfu Yang. "Numerical and Experimental Investigation on Axial Rub Impact Dynamic Characteristics of Flexible Rotor Supported by Hybrid Gas Bearings." Journal of Low Frequency Noise, Vibration and Active Control 40, no. 3 (2021): 1252–70. http://dx.doi.org/10.1177/1461348420986645.

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Gas bearings are widely used in micro- and small turbomachinery. Because of the pursuit of high efficiency, turbomachinery adopts small clearance of rotor and stator. The gas bearing rotor system easily suffers from rub impact due to the inherently low damping and load capacity of gas film. Axial rub impact may lead to catastrophic failure of gas bearing rotor system. Previous work put emphasis on radial rub, and only a few papers researched on the axial rub impact by simulation method. In this paper, dynamic responses of full annular axial rub are investigated numerically and experimentally.
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Mordanov, Sergey, Anatoly Khomyakov, Victoria Gushshamova, Elizaveta Vlasova, Mikhail Beloded, and Pavel Shkurin. "CFD simulation of unstable fluid flows in the rotor of a high-speed precipitation centrifuge." ITM Web of Conferences 59 (2024): 02014. http://dx.doi.org/10.1051/itmconf/20245902014.

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The results of a numerical study of unstable fluid flows in the rotor of a high-speed vertical precipitation centrifuge are presented. It is shown that during the operation of a high-speed precipitation centrifuge, a qualitative change in the hydrodynamic regime is possible from conditionally laminar to conditionally turbulent, characterized by large-scale axial and radial pulsations of the liquid phase, accompanied by a significant decrease in sedimentation efficiency. It has been established that the flow pulsations are not random in nature, but the amplitude of these pulsations first increa
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Shevchenko, S. S. "Mathematical modeling of centrifugal machines rotors seals for the purpose of assessing their influence on dynamic characteristics." Mathematical Modeling and Computing 8, no. 3 (2021): 422–31. http://dx.doi.org/10.23939/mmc2021.03.422.

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With an increase of equipment parameters, such as the pressure of the sealing medium and the speed of shaft rotation, the problems ensuring its hermetization efficiency are rising up. In addition to hermetization itself, the sealing system affect the overall operational safety of the equipment, especially vibratory. Groove seals are considered as hydrostatodynamic supports capable of effectively damping rotor oscillations. To determine the dynamic characteristics, models of grooved seals and single-disc rotors with grooved seals are examined. The obtained analytical dependences for computation
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Chiang, H. W. D., and S. Fleeter. "Passive Control of Flow-Induced Vibrations by Splitter Blades." Journal of Turbomachinery 116, no. 3 (1994): 489–500. http://dx.doi.org/10.1115/1.2929438.

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Splitter blades as a passive control technique for flow-induced vibrations are investigated by developing an unsteady aerodynamic model to predict the effect of incorporating splitter blades into the design of an axial flow blade row operating in an incompressible flow field. The splitter blades, positioned circumferentially in the flow passage between two principal blades, introduce aerodynamic and/or combined aerodynamic-structural detuning into the rotor. The unsteady aerodynamic gust response and resulting oscillating cascade unsteady aerodynamics, including steady loading effects, are det
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Chen, Jiajia, Fanfu Yin, Xinkai Li, et al. "Unsteady aerodynamic modelling for dual-rotor wind turbines with lifting surface method and free wake model." Journal of Physics: Conference Series 2265, no. 4 (2022): 042055. http://dx.doi.org/10.1088/1742-6596/2265/4/042055.

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Abstract A time-marching aerodynamic model for dual-rotor wind turbines (DRWT) is presented with the lifting surface method and free wake model. The performance of a reference DRWT by two axial connected NREL 5MW wind turbines is calculated to verify the algorithm. The output converges with remarkable oscillation. Free wakes swell under the coupling effect. The accumulated power of DRWT outranges single-rotor wind turbine (SRWT) by a limited extent under certain operating conditions. The front rotor (FR) produces the major portion of the power, especially for low inflow velocity. The unsteadin
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Benra, F. K. "Numerical and Experimental Investigation on the Flow Induced Oscillations of a Single-Blade Pump Impeller." Journal of Fluids Engineering 128, no. 4 (2005): 783–93. http://dx.doi.org/10.1115/1.2201629.

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This contribution is addressed to the periodically unsteady flow forces of a single-blade sewage water pump, which affect the impeller and produce radial deflections of the pump shaft. The hydrodynamic excitation forces were calculated from the time dependent flow field, which was computed by numerical simulation of the three-dimensional, viscous, time-dependent flow in the pump. A commercial computer code was used to determine the time accurate Reynolds averaged Navier-Stokes equations. The transient radial flow forces at all time steps for a complete impeller revolution affect the rotor of t
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Revaz, Tristan, and Fernando Porté-Agel. "Large-Eddy Simulation of Wind Turbine Flows: A New Evaluation of Actuator Disk Models." Energies 14, no. 13 (2021): 3745. http://dx.doi.org/10.3390/en14133745.

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Large-eddy simulation (LES) with actuator models has become the state-of-the-art numerical tool to study the complex interaction between the atmospheric boundary layer (ABL) and wind turbines. In this paper, a new evaluation of actuator disk models (ADMs) for LES of wind turbine flows is presented. Several details of the implementation of such models are evaluated based on a test case studied experimentally. In contrast to other test cases used in previous similar studies, the present test case consists of a wind turbine immersed in a realistic turbulent boundary-layer flow, for which accurate
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Xue, Qichao, Xueying Li, and Jing Ren. "Numerical Research on Flow Characteristics at High Radii of Rim Seals with Different Geometric Structures." Energies 17, no. 8 (2024): 1877. http://dx.doi.org/10.3390/en17081877.

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In the high-temperature mainstream of gas turbines, there is a rim clearance between the rotor and the stator. A rim seal is to prevent the intrusion of high-temperature gas by spraying cool fluid from the inside of the rim clearance to the outside. In the past research on rim seals, the focus was on the overall performance of the sealing structure, and the flow in the disc cavity was studied more, but the high-radius flow was simplified. In recent years, additional research in the field has focused on more complex sealing structures and high-radius flows, such as the interface between the dis
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Borovik, Sergey Yu, Valeriy P. Danilchenko, Marina M. Kuteynikova, and Yuriy N. Sekisov. "The errors of the shaft's axial movement measuring in the single-coil-eddy-current-sensors-based system for the monitoring the state of radial thrust bearing of the NK-33 liquid rocket engine’s turbopump unit." Vestnik of Samara State Technical University. Technical Sciences Series 32, no. 1 (2024): 86–101. http://dx.doi.org/10.14498/tech.2024.1.6.

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This article continues a series of publications devoted to the problems of early state diagnosis of the combined journal-and-thrust bearing of the turbo-pump unit of the liquid-propellant rocket engine NK-33, which is a critical node of the power plant under consideration. The proposed approach is based on the idea of replacing the standard induction sensors of the turbo-pump rotational speed currently used in turbo-pump unit by specially designed single-coil eddy current sensors with sensitive elements in the form of a segment of a linear conductor. The transducers are placed in the same moun
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Camp, T. R., and I. J. Day. "1997 Best Paper Award—Turbomachinery Committee: A Study of Spike and Modal Stall Phenomena in a Low-Speed Axial Compressor." Journal of Turbomachinery 120, no. 3 (1998): 393–401. http://dx.doi.org/10.1115/1.2841730.

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This paper presents a study of stall inception mechanisms in a low-speed axial compressor. Previous work has identified two common flow breakdown sequences, the first associated with a short length-scale disturbance known as a “spike,” and the second with a longer length-scale disturbance known as a “modal oscillation.” In this paper the physical differences between these two mechanisms are illustrated with detailed measurements. Experimental results are also presented that relate the occurrence of the two stalling mechanisms to the operating conditions of the compressor. It is shown that the
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Dissertations / Theses on the topic "Radial-axial oscillations of single-disk rotor"

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Гарбар, О. О. "Аналіз радіально-осьових коливань однодискового ротора". Master's thesis, Сумський державний університет, 2018. http://essuir.sumdu.edu.ua/handle/123456789/71069.

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Мета роботи – проведення аналізу радіально-осьових коливань однодискового ротору, оцінка радіальної статичної неврівноваженості, пульсацій тиску нагнітання і гармонійних змін осьової сили, діючої на ротор, оцінка критичних частот обертання ротора і амплітуди його змушених коливань. Мета дослідження – розглянути осьові коливання ротора, обумовлені його радіальними коливаннями. Тут же виводяться лінеаризовані рівняння спільних радіально-осьових коливань найпростішої одномасової моделі жорсткого ротора з автоматичним врівноважувальним пристроєм. Диск має статичну неврівноваженість. Досліджуються
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Conference papers on the topic "Radial-axial oscillations of single-disk rotor"

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Singh, Ajey, and Chetankumar S. Mistry. "Investigations on Unsteady Flow Structure Formation in Tandem Bladed Axial Flow Compressor Stage." In ASME Turbo Expo 2024: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2024. http://dx.doi.org/10.1115/gt2024-129574.

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Abstract The axial compressors suffer from the risk of flow separation upon increasing the loading beyond a certain limit due to increased boundary layer thickness on blade surface. The aerodynamic loading of axial compressors can be enhanced by implementing tandem configuration on rotor. The tandem configuration re-energizes the stalling boundary layer over blade suction surface as well as increases the overall loading of the blade. This increase in loading comes at the cost of increased blade row interaction between rotor and stator which impacts stage stability and losses. This study explor
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Peng, Caetano. "Tip Running Clearances Effects on Tip Vortices Induced Axial Compressor Rotor Flutter." In ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition. ASMEDC, 2011. http://dx.doi.org/10.1115/gt2011-45504.

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The present study aimed at investigating numerically the effects of large blade tip running clearances on flutter stability of axial core multi-stage compressor rotor. During this study, the influences of aerodynamic boundary conditions, variable stator vane incidence and tip running clearances of upstream and downstream rotors on aerodynamic compressor flow and rotor flutter stability are thoroughly investigated. The simulations were carried out using an in-house 3-D aeroelasticity code. The steady-state-solution computations are performed on single-blade-passage-one-bladerow, stage-blocks an
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Li, Du, Dazhong Lao, Ben Zhao, and Ce Yang. "Stator Wake Research in Axial-Radial Combined Compressor With Inlet Distortion." In ASME Turbo Expo 2013: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gt2013-94885.

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A combined compressor consisting of an axial rotor, a stator and a centrifugal rotor was used in a vehicle engine turbocharger because of its better performance compared with a single stage compressor under space restrictions. There have been many studies on the inlet distortion effect on multistage axial compressors; however, few studies have been performed for axial-radial combined compressors. To investigate stator wake characteristics, an axial-radial compressor was unsteadily simulated with three-dimensional Reynolds averaged Navier–Stokes equations by “domain-scaling” the rotor/stator in
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Horvath, Roland, George T. Flowers, and Jerry Fausz. "Passive Balancing for Rotor Systems Using Pendulum Balancers." In ASME 2005 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2005. http://dx.doi.org/10.1115/detc2005-84194.

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An analytical, numerical and experimental investigation of the dynamic behavior of a passive balancing system is presented. Due to the system constraints and dynamic characteristics, this system is capable of combined static and dynamic mass balancing. This work is an extension of previous studies in which ball-balancing systems were used to reduce harmful vibration caused by radial perturbation in the principal axis of inertia. In the present research, the imbalance compensation problem is divided into axial and radial components. A spherical suspension was applied at the rotational axis that
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Park, Sung-Ho, and Chong-Won Lee. "Experimental Compensation of Runout and High Order Harmonic Effects in Lorentz Force Type Integrated Motor-Bearing System." In ASME 2005 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2005. http://dx.doi.org/10.1115/detc2005-85483.

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An integrated motor-bearing system integrates the functions of an active magnetic bearing and an electric motor into a single unit. Because this system requires the simultaneous generation of torque and radial control force, there will inevitably be undesired high order harmonic components in the rotating magnetic field, which will result in torque ripple and radial force distortion. Sensor target runout is a severe excitation source and, as such, causes a lot of vibration. In this paper, we propose an experimental compensation procedure for the oscillation and coupling of torque and radial fo
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Stasenko, David, Nikhil Rao, and Diganta Narzary. "Thrust Force Measurements in an Axial Steam Turbine Test Rig." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-14673.

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Abstract Large mechanical drive steam turbines used in the oil & gas industry are operating at increasingly higher inlet pressure, generating higher shaft power. Those higher power requirements result in larger disk diameters and surface areas. High thrust forces can be a result, due to both the high inlet pressure and large disk surface area. Industry standards require oversizing of thrust bearings to handle uncertainty in thrust predictions. These factors make improvement in thrust prediction accuracy and mitigation strategies important. A full-size, axial flow steam turbine test rig cap
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Nie, Chaoqun. "An Experimental Investigation on Different Radial Loading Distribution and Patterns of Stall Inception in a Single-Stage Low-Speed Axial Compressor." In ASME Turbo Expo 2003, collocated with the 2003 International Joint Power Generation Conference. ASMEDC, 2003. http://dx.doi.org/10.1115/gt2003-38090.

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Recent research efforts have focused on the aerodynamic mechanism, identifications, and advanced capturing methods of stall inception. Making use of active control and intelligent casing treatment, all the efforts aim at expanding operational ranges of compressors and at improving their operational stability. It is widely known that the dynamic behavior of stall inception is strongly influenced by occurrence of inlet distortion, radial loading distribution, tip-clearance flow, stage matching, and downstream oscillation from combustion chambers. Therefore, experimental research is imperative to
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Diemel, Eric, Stefan Odenbach, Wieland Uffrecht, Jose Rey Villazon, Antonio Guijarro Valencia, and Mike Reinecke. "High Speed Single Cavity Rig With Axial Throughflow of Cooling Air: Rig Structure and Periphery." In ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gt2019-91265.

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Abstract Appropriate understanding of heat transfer and temperature distribution of gas-turbine compressor disks is very important for mechanical rotor design. Accurate prediction of disk metal temperatures is key to ensure safe operation and furthermore rotor tip clearances has a significant influence on the compressor efficiency. Despite great improvements in the prediction of fluid motion and heat transfer in complex systems, the increasingly demanding requirement for more efficient compressors demands more accurate understanding of the flow around those disks. Therefore, a research rig has
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Narzary, Diganta, David Stasenko, and Nikhil Rao. "Thrust Force Measurements in an Axial Steam Turbine Test Rig: Effect of Disk Balance Holes." In ASME Turbo Expo 2021: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2021. http://dx.doi.org/10.1115/gt2021-59242.

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Abstract A full-size, full-speed, axial flow steam turbine test rig capable of measuring turbine thrust, and static pressures in the rotor-stator disk cavity was built and commissioned. The test rig was operated in a single-stage configuration for the test results first reported in Stasenko et al. [1], and now in this paper. The stage has stationary axial face seals radially inward of the airfoils, near the rotor disk rim. The face seals divide the rotor-stator cavity into inner and outer circumferential cavities, both of which were instrumented with static pressure probes on the stator radial
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Balasubramanian, J., M. Michael, R. P. Roy, Y. W. Kim, and H. K. Moon. "Experiments on Front- and Aft- Disk Cavity Ingestion in a Subscale 1.5-Stage Axial Turbine." In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-56214.

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This paper describes experiments performed in a subscale 1.5-stage axial air turbine in which ingestion of mainstream air into the front and aft disk cavities was measured. The front disk cavity is upstream of the rotor, the aft disk cavity is downstream of the rotor. Both disk cavities contain a labyrinth seal at a radially inboard location; this seal divides the cavity into a ‘rim cavity’ and an ‘inner cavity’. The front rim cavity features a double seal with radial clearance and axial overlap at its periphery; the aft rim cavity double seal possesses axial gap. Results are reported for thre
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