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1

Al-Rawashdeh, Ayman Y., Ali Dalabeeh, Abdallah Al-Zeyod, Ashraf Samarah, Ghazi Qaryouti, and Omar Albarbarawi. "The tooth factor effect on the harmonics of large electrical machines." Bulletin of Electrical Engineering and Informatics 9, no. 4 (2020): 1677–84. http://dx.doi.org/10.11591/eei.v9i4.1565.

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In the current study, the general mathematical model for the calculation and analysis of asynchronous systems and transient cases in asynchronous synchronous large electrical machines was developed. The theory of magnetic fields in the teeth's circuits with a smooth surface of the rotor was used and at the same time, high harmonics of magnetic fields and its effect on the transient cases was also calculated. Performance curves were investigated using Matlab codes and evaluated under different values of factor. The results confirmed the possibility of improving the noise harmonics on the sinusoidal wave form, which is reflected on the machines starting.
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2

Świrydczuk, Jerzy. "Wake-blade interaction in steam turbine stages." Polish Maritime Research 20, no. 2 (2013): 30–40. http://dx.doi.org/10.2478/pomr-2013-0014.

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Abstract The article discusses the phenomenon of stator Wake/Rotor cascade (W/R) interaction in a steam turbine stage, and the ability to capture it in turbine stage design calculations making use of standard numerical codes. Firstly, the W/R interaction is analysed by comparing its real, experimentally recorded course with the numerical results obtained using vortex theory models and methods. This part of the analysis ends with formulating a conclusion about stochastic nature of the W/R interaction and indicating its reason, which is the vortex structure of the stator wake. Next, a question is discussed whether and how this stochastic nature of the examined phenomenon can be taken into account in calculations of Reynolds Averaged Navier-Stokes (RANS) equations. Differences are indicated between the uniform pattern of the stator wake obtained using a RANS code and the vortex structure of the real wake. It is concluded, however, that despite these differences the RANS results correctly reflect the time-averaged course of the real W/R interaction, and the process of averaging the flow parameters on the sliding plane between stator and rotor calculation areas can be treated as sort of “numerical averaging” of different realisations of the W/R interaction.
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3

Boorsma, Koen, Florian Wenz, Koert Lindenburg, Mansoor Aman, and Menno Kloosterman. "Validation and accommodation of vortex wake codes for wind turbine design load calculations." Wind Energy Science 5, no. 2 (2020): 699–719. http://dx.doi.org/10.5194/wes-5-699-2020.

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Abstract. The computational effort for wind turbine design load calculations is more extreme than it is for other applications (e.g., aerospace), which necessitates the use of efficient but low-fidelity models. Traditionally the blade element momentum (BEM) method is used to resolve the rotor aerodynamic loads for this purpose, as this method is fast and robust. With the current trend of increasing rotor size, and consequently large and flexible blades, a need has risen for a more accurate prediction of rotor aerodynamics. Previous work has demonstrated large improvement potential in terms of fatigue load predictions using vortex wake models together with a manageable penalty in computational effort. The present publication has contributed towards making vortex wake models ready for application to certification load calculations. The observed reduction in flapwise blade root moment fatigue loading using vortex wake models instead of the blade element momentum (BEM) method from previous publications has been verified using computational fluid dynamics (CFD) simulations. A validation effort against a long-term field measurement campaign featuring 2.5 MW turbines has also confirmed the improved prediction of unsteady load characteristics by vortex wake models against BEM-based models in terms of fatigue loading. New light has been shed on the cause for the observed differences and several model improvements have been developed, both to reduce the computational effort of vortex wake simulations and to make BEM models more accurate. Scoping analyses for an entire fatigue load set have revealed the overall fatigue reduction may be up to 5 % for the AVATAR 10 MW rotor using a vortex wake rather than a BEM-based code.
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4

Nalim, M. R., and E. L. Resler. "Wave Cycle Design for Wave Rotor Gas Turbine Engines With Low NOx Emissions." Journal of Engineering for Gas Turbines and Power 118, no. 3 (1996): 474–80. http://dx.doi.org/10.1115/1.2816670.

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The wave rotor is a promising means of pressure-gain for gas turbine engines. This paper examines novel wave rotor topping cycles that incorporate low-NOx combustion strategies. This approach combines two-stage “rich-quench-lean” (RQL) combustion with intermediate expansion in the wave rotor to extract energy and reduce the peak stoichiometric temperature substantially. The thermodynamic cycle is a type of reheat cycle, with the rich-zone air undergoing a high-pressure stage. Rich-stage combustion could occur external to or within the wave rotor. An approximate analytical design method and CFD/combustion codes are used to develop and simulate wave rotor flow cycles. Engine cycles designed with a bypass turbine and external combustion demonstrate a performance enhancement equivalent to a 200–400 R (110–220 K) increase in turbine inlet temperature. The stoichiometric combustion temperature is reduced by 300–450 R (170–250 K) relative to an equivalent simple cycle, implying substantially reduced NOx formation.
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5

Manke, Joseph W., Joel E. Hirsh, Byung K. Oh, Thomas M. Wicks, and Leo Dadone. "Improved rotor tip-relief modeling by coupling comprehensive rotor analysis and rotor aerodynamics codes." Advances in Engineering Software 29, no. 3-6 (1998): 475–80. http://dx.doi.org/10.1016/s0965-9978(98)00043-x.

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6

Zhao, Jia Quan, Da Peng Hu, Pei Qi Liu, Feng Xia Liu, and Jin Ji Gao. "Thermodynamic Analysis a Novel Wave Rotor Refrigeration Cycle." Advanced Materials Research 805-806 (September 2013): 537–42. http://dx.doi.org/10.4028/www.scientific.net/amr.805-806.537.

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As a novel generation of thermal separators, the Wave rotor refrigerator (WRR) has replaced the traditional pressure-wave thermal separator. However, the isentropic refrigeration efficiency still needs to be improved compared with expander. A novel WRR system cycle was built and the system performance was thermal analyzed under various parameters, such as expansion efficiency or compression efficiency of wave rotor. The results are used to compare with the traditional WRR system. It is shown that the advantage provided by this novel cycle over the traditional WRR is an expansion process and a compression process is integrated into one unit, with a higher energy transfer efficiency and simple structure. The isentropic refrigeration efficiency of this novel cycle can be more than twice of the traditional WRR under the pressure ratio of 1.1. The experimental works are carrying out.
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7

Arkharov, A. M., V. Yu Semenov, S. B. Malakhov, and A. I. Savitskii. "Analysis of working processes in a rotor-wave cryogenerator." Chemical and Petroleum Engineering 48, no. 7-8 (2012): 420–28. http://dx.doi.org/10.1007/s10556-012-9634-z.

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8

Atanasiu, Catalin George, and Daniel Eugen Buzea. "Researches Regarding Modal Analysis of a Pressure Wave Supercharger Rotor." Applied Mechanics and Materials 332 (July 2013): 319–24. http://dx.doi.org/10.4028/www.scientific.net/amm.332.319.

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This paper aims on comparison between virtual modal analysis and experimental modal analysis of a PWS rotor. A virtual simulation and an experimental analysis were conducted in order to successfully determine the eigen modes of the PWS rotor. Those frequencies are a good thing to know in case of a new PWS development.
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9

Welch, G. E., S. M. Jones, and D. E. Paxson. "Wave-Rotor-Enhanced Gas Turbine Engines." Journal of Engineering for Gas Turbines and Power 119, no. 2 (1997): 469–77. http://dx.doi.org/10.1115/1.2815598.

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The benefits of wave rotor topping in small (300- to 500-kW [400- to 700-hp] class) and intermediate (2000- to 3000-kw [3000- to 4000-hp] class) turboshaft engines, and large (350- to 450-kN [80,000- to 100,000-lbf] class) high-bypass-ratio turbofan engines are evaluated. Wave rotor performance levels are calculated using a one-dimensional design/analysis code. Baseline and wave-rotor-enhanced engine performance levels are obtained from a cycle deck in which the wave rotor is represented as a burner with pressure gain. Wave rotor topping is shown to enhance the specific fuel consumption and specific power of small- and intermediate-sized turboshaft engines significantly. The specific fuel consumption of the wave-rotor-enhanced large turbofan engine can be reduced while it operates at a significantly reduced turbine inlet temperature. The wave-rotor-enhanced engine is shown to behave off-design like a conventional engine. Discussion concerning the impact of the wave rotor/gas turbine engine integration identifies technical challenges.
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10

Kablitz, Stephan, Jörg Bergner, Dietmar K. Hennecke, Manfred Beversdorff, and Richard Schodl. "Darmstadt Rotor No. 2, III: Experimental Analysis of an Aft-Swept Axial Transonic Compressor Stage." International Journal of Rotating Machinery 9, no. 6 (2003): 393–402. http://dx.doi.org/10.1155/s1023621x0300037x.

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At Darmstadt University of Technology (Darmstadt, Germany), the Department of Gas Turbines and Flight Propulsion operates a single-stage transonic compressor test stand. Its main purpose is to provide a database for the validation of computational fluid dynamics codes. In addition, it serves as a testbed for new materials and also for the development of new measurement techniques. After setting up the test rig with a baseline rotor (Rotor No. 1), a titanium bladed disk with conventional radially stacked blade sections, a new rotor (Rotor No. 2) was designed, with the addition of considerable amounts of aft sweep and backward lean. The new rotor's flow field and mechanical properties were investigated by using various measurement techniques, including a laser-2-focus setup.
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11

Yang, Kang, and Yi Yang. "Application of FEM Analysis to Fault Diagnosis of Cracked Rotor." Applied Mechanics and Materials 37-38 (November 2010): 181–84. http://dx.doi.org/10.4028/www.scientific.net/amm.37-38.181.

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Based on the simple crack model and the finite element method (FEM) theorem, the corresponding dynamic equation of the cracked rotor based on FEM analysis is modeled and the numerical simulation solutions are obtained. By analyzing the dynamic characteristics of cracked rotor in diverse conditions, the properties of the un-cracked rotor and cracked rotor are discussed. A valid fault diagnosis method of cracked rotor is purposed. The method demonstrates that the cracked rotor can be identified by estimating if the swing of disk center obviously accretion and appear wave crest when rotate speed is a half critical speed of rotor shaft system.
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12

Xiao, Yanjia, Xiaobin Ji, Beijiang Liu, and Xi’an Xiong. "Partial wave analysis with OpenAcc." EPJ Web of Conferences 245 (2020): 06040. http://dx.doi.org/10.1051/epjconf/202024506040.

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Partial wave analysis(PWA) is an important tool in hadron physics. Large data sets from the experiments in high precision frontier require high computational power. To utilize GPU cluster and the resource of super computers with various types of accelerator, we implement a software framework for partial wave analysis using OpenAcc, OpenAccPWA. OpenAccPWA provides convenient approaches for exposing parallelism in the code and excellent support for the large amount of existing CPU-based codes of partial wave amplitudes. It can avoid heavy workload of code migration from CPU to GPU. This proceeding will briefly introduce the software framework and performance of OpenAccPWA.
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13

Hill, G. F. J., and P. M. Weaver. "Analysis of anisotropic prismatic sectiosn." Aeronautical Journal 108, no. 1082 (2004): 197–205. http://dx.doi.org/10.1017/s0001924000000105.

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The dynamic behaviour of rotor blades is often modelled using onedimensional beam analysis with equivalent mass and stiffness properties to those of the full blade. Calculation of accurate elastic stiffness terms for these arbitrarily shaped sections with differing material properties is vital to this process. A method which produces these properties using standard finite element analysis codes is presented. The method is then compared with theoretical results for a simple rectangular section beam and case studies are performed on a composite laminate and box-section.
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14

CHEN, LONG, YIZHAO WU, and JIAN XIA. "AEROELASTIC ANALYSIS OF ROTOR BLADES USING CFD/CSD COUPLING IN HOVER MODE." Modern Physics Letters B 24, no. 13 (2010): 1307–10. http://dx.doi.org/10.1142/s0217984910023499.

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A computational fluid dynamics (CFD) is coupled with a computational structural dynamics (CSD) to simulate the unsteady rotor flow with aeroelasticity effects. An unstructured upwind Navier-Stokes solver was developed for this simulation, with 2nd order time-accurate dual-time stepping method for temporal discretization and low Mach number preconditioning method. For turbulent flows, both the Spalart-Allmaras and Menter's SST model are available. Mesh deformation is achieved through a fast dynamic grid method called Delaunay graph map method for unsteady flow simulation. The rotor blades are modeled as Hodges & Dowell's nonlinear beams coupled flap-lag-torsion. The rotorcraft computational structural dynamics code employs the 15-dof beam finite element formulation for modeling. The structure code was validated by comparing the natural frequencies of a rotor model with UMARC. The flow and structure codes are coupled tightly with information exchange several times at every time step. A rotor blade model's unsteady flow field in the hover mode is simulated using the coupling method. Effect of blade elasticity with aerodynamic loads was compared with rigid blade.
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15

Castells, Camille, François Richez, and Michel Costes. "A Numerical Analysis of the Dynamic Stall Mechanisms on a Helicopter Rotor from Light to Deep Stall." Journal of the American Helicopter Society 65, no. 3 (2020): 1–17. http://dx.doi.org/10.4050/jahs.65.032005.

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A loose coupling methodology between computational fluid dynamics and Comprehensive Analysis codes (elsA/HOST) is used to simulate a helicopter rotor in dynamic stall condition. Three stalled forward flight conditions have been selected in the wind tunnel 7A rotor test data to investigate the evolution of the stall mechanisms from a light stall to a deep stall condition. A decrease in the RPM is used to increase the rotor load. The lower the RPM the more severe the stall is. A double stall is observed in the lowest RPM case. The simulations are in satisfactory agreement with the experiment and are used to identify the mechanisms leading to the different stall events, notably the blade–vortex interaction. Rotormaps of the flow-separation regions are computed from numerical results, and similar regions of separated flow are observed in all the cases. These flow-separations originate from different aeroelastic mechanisms depending on their position on the rotor disk. As the rotor thrust coefficient is increased, some of these flow separations grow and lead to stall events.
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16

Bogacz, R., T. Szolc, and H. Irretier. "An Application of Torsional Wave Analysis to Turbogenerator Rotor Shaft Response." Journal of Vibration and Acoustics 114, no. 2 (1992): 149–53. http://dx.doi.org/10.1115/1.2930243.

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In this paper transient torsional vibrations of a steam turbogenerator rotor shaft system due to high speed reclosing of the electric network are investigated. The analysis is performed using torsional elastic wave theory applied to a continuous model in the form of a stepped shaft. Wave solutions of the equations of motion are used in order to determine dynamic torsional elastic moments and vibratory angular velocities in cross-sections of the turbine shafts. The results are illustrated in the form of graphs.
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17

Poguluri, Sunny Kumar, Dongeun Kim, Haeng Sik Ko, and Yoon Hyeok Bae. "Performance Analysis of Multiple Wave Energy Converters due to Rotor Spacing." Journal of Ocean Engineering and Technology 35, no. 3 (2021): 229–37. http://dx.doi.org/10.26748/ksoe.2021.007.

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18

Yang, Kang, and Yi Yang. "Simulation of Crack Dynamic Characteristics of Rotor Based on FEM Analysis." Advanced Materials Research 139-141 (October 2010): 2677–80. http://dx.doi.org/10.4028/www.scientific.net/amr.139-141.2677.

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A new simulation method is proposed for dynamic characteristics of cracked rotor based on the finite element analysis, in which the stiffness model has been derived for the exact description of variation rules of cracked shafts. A non-linear dynamic equation is constituted according to stiffness characteristic of cracked-rotor change in time domain. Then the corresponding dynamic equation of the cracked rotor based on FEM analysis is modeled and the numerical simulation is carried out with solutions of high accuracy. At last, the dynamic characteristics of cracked rotor in diverse conditions are analyzed, and the simulation results are compared. It is shown that the non-linear oil film bearing force coupling with periodicity variety stiffness of cracked rotor has a great effect on dynamic behavior of the rotor and that the cracked rotor can be diagnosed effectively by the criterion that the swing of disk center obviously accretes and the wave crest appears when rotation speed is a half critical speed of rotor shaft system.
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19

Hu, Dong Dong, Yan Jun Liu, Li Kang Hong, and Xiao Chen Guo. "Finite Element Analysis for Water Turbine of Horizontal Axis Rotor Wave Energy Converter." Applied Mechanics and Materials 530-531 (February 2014): 906–10. http://dx.doi.org/10.4028/www.scientific.net/amm.530-531.906.

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Horizontal axis rotor wave energy converter is a new form for utilization of ocean wave energy, and the axis of its water turbine is parallel with the sea level and perpendicular to the direction of wave. This paper employed the linear wave theory and Froude-Krylov presumptive method to calculate the wave force, which was exerted on the wave energy converter in extremely arduous wave conditions. The finite element research on the deformation and the stress response of the water turbine was carried out to assess its security. The results show that the deformation and the stress responses both reach their maximum values at the 3rd mode shape about 90Hz, and the deformation response is 0.4208mm and the stress response is 0.8052MPa at this frequency, which are both within the required security range.
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20

Wang, Rui, Xinglin Guo, and Yuefang Wang. "Nonlinear analysis of rotor system supported by oil lubricated bearings subjected to base movements." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 230, no. 4 (2015): 543–58. http://dx.doi.org/10.1177/0954406215578704.

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Response analysis of rotor system subjected to the base movements in a large rotational machinery is a complex high-dimensional nonlinear problem. In this paper, rotor system of a centrifugal pump with a pair of oil lubricated bearings is modeled as a six-degrees-of-freedom nonlinear system by the Lagrange method. The Runge–Kutta–Felburg method with variable step size is applied to solve the equations based both on nonlinear bearing model and on linearized bearing model. Poincaré maps, phase trajectories, bifurcation diagrams, and cascade diagrams are used to illustrate the dynamics of the rotor with the two bearing models. The responses of these two kinds of systems under El Centro seismic wave are obtained. The acceleration data of the seismic wave are used as the input of base movements. The short bearing model is applied to express the nonlinear oil film force. Compared to the system with model of linearized bearing, the nonlinear bearing–rotor system can accurately reflect the dynamics of the system. Furthermore, trigonometric functions are employed to express the base movements, and the responses of nonlinear bearing–rotor system subject to the base movements are obtained. The fast Fourier transform is used to analyze the nonlinear bearing–rotor system with effects of the base movements. The results reveal not only the dynamic behavior of the rotor of the centrifugal pump supported by two nonlinear bearings, but also the responses of the nonlinear bearing–rotor system with the combined effects of centrifugal force and base movements.
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21

Adiletta, Giovanni, Erasmo Mancusi, and Salvatore Strano. "Nonlinear behavior analysis of a rotor on two-lobe wave journal bearings." Tribology International 44, no. 1 (2011): 42–54. http://dx.doi.org/10.1016/j.triboint.2010.08.009.

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22

Subrahmanyam, V., and V. Mouly. "Analysis of an induction motor with square wave currents in the rotor." Canadian Electrical Engineering Journal 10, no. 1 (1985): 40–45. http://dx.doi.org/10.1109/ceej.1985.6593137.

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23

Wang, Haifei, and Chen Chen. "Stability analysis of a rotor system with fluid applying wave resonance theory." Physics of Fluids 32, no. 5 (2020): 054106. http://dx.doi.org/10.1063/5.0011578.

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24

Yang, Weichao, Yanrong Wang, Xianghua Jiang, and Xiaobo Zhang. "Flutter analysis of a one-and-a-half-stage fan at low speed using nonlinear harmonic method." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 234, no. 8 (2020): 1380–94. http://dx.doi.org/10.1177/0954410020904862.

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Multirow effects on flutter stability of a 1.5-stage fan at low speed are investigated using nonlinear harmonic method in a one-way coupled fashion. In the first part, the mesh-independence verification and validation of nonlinear harmonic method to simulate multirow effects are performed. In the second part, multirow effects are separated into two parts including acoustic reflection and rotor–stator interaction induced by relative motion between rotor and stators with each part investigated individually. Effect of acoustic reflection from upstream and downstream blade rows is investigated separately using a harmonic truncation method to avoid the change of time-mean flow. The results show that acoustic reflection can have a large effect on flutter stability of rotor blade. The simulation of the rotor–stator interaction effect indicates that the rotor–stator interaction does not significantly affect the flutter stability of rotor blade in this case. Lastly, the variation of aerodynamic modal damping ratio with the size of gap between inlet guide vane and rotor is investigated. Aerodynamic modal damping ratio at a nodal diameter whose fundamental mode is cut-on varies periodically with gap size. Wave splitting method is employed to further investigate the relation between the phase difference between incoming and outgoing wave and aero damping, which can be used to improve the flutter stability at the design stage.
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25

Saxer, A. P., and H. M. Felici. "Numerical Analysis of Three-Dimensional Unsteady Hot Streak Migration and Shock Interaction in a Turbine Stage." Journal of Turbomachinery 118, no. 2 (1996): 268–77. http://dx.doi.org/10.1115/1.2836636.

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A three-dimensional unsteady flow computation has been performed for a transonic first turbine stage under the influence of streaks of hot gas exiting the combustion chamber. Realistic flow conditions are obtained by using an unequal stator-to-rotor pitch, a single-streak/multistator channel configuration, and periodic boundary conditions. The resulting unsteady shock wave system and the hot streak migration as well as the shock wave/streak interaction are presented and discussed. In addition, the time average of the periodic unsteady solution is analyzed and compared with a steady-state computation. The steady-state solution is analyzed and compared with a steady-state computation. The steady-state solution matches the time-averaged one in terms of the pressure field and the maximum stagnation temperature on the rotor blade surface. However, the rotor blade temperature patterns are different with a stronger radial secondary flow present in the time-averaged solution due to the retention of the circumferential streak variations at the stator/rotor interface.
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26

Hu, Shu Ju, Ling Ling Wang, and Ya Deng. "Analysis on Power Output Capability and its Power Control Strategy of DFIG Wind Turbine under Unbalanced Grid Voltage." Applied Mechanics and Materials 448-453 (October 2013): 1819–24. http://dx.doi.org/10.4028/www.scientific.net/amm.448-453.1819.

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Wind turbines are required by gird codes that active and reactive power should be fed into power grid during gird faults such as voltage sags. Power output capability is important for DFIG wind turbine to provide active and reactive power support. Constraints of stator, rotor maximum current and maximum output voltage of rotor-side converter (RSC) of DFIG are considered to analyze stator power output limit of the DFIG under unbalanced voltage sags, and newton-raphson method is used to solve the power limits, then the power control strategy based on power limit analysis is proposed. Simulation, calculation and comparison are carried out by a 1.5MW DFIG wind turbine model, and the effectiveness of the analysis and the proposed control strategy is verified.
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27

Wood, J. R., J. F. Schmidt, R. J. Steinke, R. V. Chima, and W. G. Kunik. "Application of Advanced Computational Codes in the Design of an Experiment for a Supersonic Throughflow Fan Rotor." Journal of Turbomachinery 110, no. 2 (1988): 270–79. http://dx.doi.org/10.1115/1.3262191.

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Increased emphasis on sustained supersonic or hypersonic cruise has revived interest in the supersonic throughflow fan as a possible component in advanced propulsion systems. Use of a fan that can operate with a supersonic inlet axial Mach number is attractive from the standpoint of reducing the inlet losses incurred in diffusing the flow from a supersonic flight Mach number to a subsonic one at the fan face. The data base for components of this type is practically nonexistent; therefore, in order to furnish the required information for assessment of this type fan, a program has been initiated at the NASA Lewis Research Center to design, build, and test a fan rotor that operates with supersonic axial velocities from inlet to exit. This paper describes the design of the experiment using advanced computational codes to calculate the unique components required. The fan rotor has constant hub and tip radii and was designed for a pressure ratio of 2.7 with a tip speed of 457 m/s. The rotor was designed using existing turbomachinery design and analysis codes modified to handle fully supersonic axial flow through the rotor. A two-dimensional axisymmetric throughflow design code plus a blade element code were used to generate fan rotor velocity diagrams and blade shapes. A quasi-three-dimensional, thin shear layer Navier–Stokes code was used to assess the performance of the fan rotor blade shapes. The final design was stacked and checked for three-dimensional effects using a three-dimensional Euler code interactively coupled with a two-dimensional boundary layer code. A translating nozzle was designed to produce a uniform flow parallel to the fan up to the design axial Mach number of 2.0. The nozzle was designed with the three-dimensional Euler/interactive boundary layer code. The nozzle design in the expansion region was analyzed with a three-dimensional parabolized viscous code, which corroborated the results from the Euler code. A translating supersonic diffuser was designed using these same codes.
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28

Ikhwan, Muhammad, Syamsul Rizal, Marwan Ramli, Zainal A. Muchlisin, and Said Munzir. "Hydrodynamics and Tidal Turbine Generator Stability Analysis in Several Wave Variations." International Journal of Differential Equations 2021 (June 16, 2021): 1–8. http://dx.doi.org/10.1155/2021/6682407.

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The development of tidal turbines continues to be carried out by many researchers, including the incorporation of a control system for optimization purposes. This paper attempts to assess the stability of two mechanical systems in a tidal turbine: a propeller harvesting kinetic energy and a d-q diagram system on a permanent-magnet synchronous generator (PMSG). The method employed is the representation of a phase plane profile with a stable eigenvalue. The critical value of the turbine’s rotations per minute provides some points of equilibrium. The effect of the angular velocity singular on the modified system was also investigated. There is no cutoff control for the generator rotational speed in the case of weak currents, according to the results. The combination of the three tidal turbine components results in a shift in the equilibrium point. Although PMSG has an infinite equilibrium point along the line Id = 0, the effect of the rotor angular velocity prevents all of these points from being in equilibrium. Finally, in this study, the rotor angular velocity caused by the speed and type of ocean currents are only the upper and lower limits. The stability of the various wave variations is within this range.
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29

Wang, Hong Li, Bing Xu, Xue Dong Xue, and Kan Cheng. "Application of Time-Frequency Analysis & Blind Source Separation to Diagnosis of Faults with Generator Rotor System." Applied Mechanics and Materials 556-562 (May 2014): 2748–51. http://dx.doi.org/10.4028/www.scientific.net/amm.556-562.2748.

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One method for diagnosis of faults with generator rotor is contrived by combining local wave method and blind source separation. Time-frequency image varies with local wave of different fault signals, and this feature is applied to identify different faults. In order to realize automatic classification of faults, blind source separation is employed for separation of independent components in time-frequency image of local wave of different fault signals, so as to derive projection coefficients for a set of source images. On the basis of this, automatic classification of faults is realized with probability nerve network. Taking fault signal of rotor as an example, this method is investigated, and the validity is proved by experimental results.
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30

Yoda, Kiyoshi. "Analysis of Experimental XAFS Data Using Curved-Wave, Single-Scattering XAFS Codes." Japanese Journal of Applied Physics 32, S2 (1993): 128. http://dx.doi.org/10.7567/jjaps.32s2.128.

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31

Inoue, J., Y. Jinnouchi, and Y. Araki. "Forced Wave Motion of Liquid Partially Filling a High-Speed Rotor." Journal of Vibration and Acoustics 107, no. 4 (1985): 446–52. http://dx.doi.org/10.1115/1.3269286.

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Wave motion of a liquid in a partially filled hollow cylindrical rotor, which rotates at a high speed and is forced to vibrate, is theoretically and experimentally investigated. Main emphasis is placed on the analysis of a large wave motion in the liquid which may cause self-excited vibrations of the rotor. Assuming a thin liquid layer, simplified equations of motion are derived by integration of the governing equations for a two-dimensional flow. Nonlinearity and viscosity are taken into account in the analysis. A large wave motion with a broken wavecrest is analyzed by applying a theory of hydraulic jump. Illustrating typical examples of the theoretical results together with the experimental ones, the dynamic behavior of the liquid motion and the basic relations between the liquid force and the rotor vibration are discussed.
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32

Wu, Yanhui, Guangyao An, Zhiyang Chen, and Bo Wang. "Computational analysis of vortices near casing in a transonic axial compressor rotor." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 2 (2017): 710–24. http://dx.doi.org/10.1177/0954410017740922.

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Complicated flowfields near casing in a transonic axial flow compressor rotor have been numerically investigated in this paper. Two vortex identification methods, namely the Eigenvector Method and Lambda 2 Method, are introduced as important tools for the graphical representation of the concentrated vortices arising from tip leakage flow and blade boundary layer separation. The analysis of the numerical results reveals that multiple tip vortices whose development are dependent on the variation of shock wave configuration are observed at conditions around the peak efficiency point. However, with the decrease of the massflow rate, only the well-known tip leakage vortex and the second tip vortex are left in the tip region due to the disappearance of the second shock wave. Then when the massflow rate further decreases to the stall limit, an deceleration flow region emerges downstream of the shock wave due to an increasing interaction between the first shock wave and the well-known tip leakage vortex. The tip leakage vortex further experiences a bubble-type and then spiral-type breakdown at near stall flow conditions. In addition, the validity of the two vortex identification methods is also discussed in this paper. It is found that both methods are able to identify and accentuate the concentrated streamwise vortices near casing when a vortex is not disrupted. However, if the vortex breakdown occurs, only Eigenvector Method can describe the breakdown region in a deep view.
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33

Zhang, Jun Hong, Liang Ma, Jie Wei Lin, and Gui Chang Zhang. "Dynamic Analysis of Flexible Rotor-Ball Bearings System with Unbalance-Misalignment-Rubbing Coupling Faults." Applied Mechanics and Materials 105-107 (September 2011): 448–53. http://dx.doi.org/10.4028/www.scientific.net/amm.105-107.448.

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Dynamic responses of flexi rotor-ball-bearing system under unbalance misalignment rubbing coupling faults are studied. Coupling faults dynamic control model of flexi-multi-system of rotor-ball-bearing system is established, based on finite element analysis and numerical integral combined simulate method. Then nonlinear bearing force and rub-impact force models are programmed in MATLAB. Analysis and compare vibration characteristics of system while under faults-free, unbalance and rub-impact faults. The result demonstrates that when system under unbalance faults, vibration frequency brought by eccentric mass is agreed with rotating speed frequency, its fundamental frequency wave add high frequency component, can show the characteristics of unbalance-rubbing faults efficiently; when system under misalignment faults, with frequency double vibration and high harmonics; when system under unbalance-misalignment-rubbing coupling faults, support force of shafting of rotor system appears high frequency responses like saw tooth based on sine wave, causing aggravation of rub-impact faults.
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34

Pan, Ruochi, Zhaoyun Song, and Bo Liu. "Optimization Design and Analysis of Supersonic Tandem Rotor Blades." Energies 13, no. 12 (2020): 3228. http://dx.doi.org/10.3390/en13123228.

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To explore the flow mechanism and improve the performance of supersonic tandem rotor blades, the supersonic rotor Rotor37 is taken as the prototype and redesigned to an original supersonic tandem rotor. Then, based on the Kriging model, the physical programming method, and improved particle swarm optimization algorithm, a multi-objective optimization methodology is developed and applied to achieve the multi-objective optimization of the supersonic tandem rotor blades. Compared with Rotor37, the mass flow and surge margin of the original tandem rotor obviously increased. However, the efficiency of the original tandem rotor was slightly lower than Rotor37. After multi-objective optimization, compared with the original tandem rotor, the total pressure ratio and efficiency of the optimized tandem rotor significantly increased, and the efficiency increased by 1.6%. Further, the surge margin increased by 2.75%. The range and intensity of the high-loss region in the middle section of the optimized tandem rotor significantly decreased, and the range of the low-loss area in the middle region and tip region significantly increased, but the range and strength of the high-loss area in the tip region changed a little. The reason for the decrease of total pressure loss in the middle region and tip region is that the three-dimensional optimization of the blade significantly reduced the shock loss and boundary layer separation loss of the front blade. At the same time, the mixing loss between low energy fluid and the main flow in blade wake also reduced. Besides, the three-dimensional optimization of the blade had little impact on the leakage flow and the secondary flow generated by the mutual interference of the leakage flow and shock wave.
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35

Qiao, Zhaowei, and Yutian Sun. "Analysis of Electromagnetic Force on Rotor End Windings of a 300 MW Variable-Speed Generator Motor for Pumped Storage." Mathematical Problems in Engineering 2020 (May 5, 2020): 1–6. http://dx.doi.org/10.1155/2020/6493581.

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The variable-speed generator motor (VSGM) for pumped storage has a cylindrical rotor with three-phase lap or wave windings distributed in slots evenly and fed by a converter. For a large-scale VSGM, the electromagnetic force (EMF) on rotor end windings is an important contributor to distortion, vibration, and even damage of rotor end windings. A 3D finite element model of rotor end region of a 300 MW VSGM is set up. The distribution map of EMF density on involute and nose parts of rotor end windings, under rated load and three-phase short circuit at supersynchronous and subsynchronous speed, is drawn. Furthermore, the amplitude of EMF is calculated, and the radial, tangential, and axial components of EMF are analyzed. The results in this paper will lay a foundation for design of rotor end windings and their support structure.
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36

Xiao, Hai Yan, Xue Wu Wang, and Deng Feng Chen. "Fault Diagnose of Rotor Winding Inter Turn Short Circuit in Generator." Applied Mechanics and Materials 321-324 (June 2013): 1290–94. http://dx.doi.org/10.4028/www.scientific.net/amm.321-324.1290.

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Based on magnetic characteristics of inter turn circuit of rotor windings in turbo generator, and analysis the principles of detecting coil method. Based on the symmetry of generator structure and magnetic character between stator and rotor, three fault diagnose methods are presented in this paper: Wave form limitations, Half-wave sliding superposition and Reference wave forms. The application example shows that Reference wave forms method is capable of diagnosing inter turn fault, its severity, and especially locating the inter turn short circuit fault.
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37

Hendricks, Robert C., Jack Wilson, Tom Y. Wu, Ralph Flower, and Robert L. Mullen. "Bidirectional Brush Seals – Post-Test Analysis." International Journal of Rotating Machinery 5, no. 3 (1999): 167–80. http://dx.doi.org/10.1155/s1023621x99000159.

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A post-test analysis of a set of inside-diameter/outside-diameter (ID/OD) bidirectional brush seals used in three-port wave rotor tests was undertaken to determine brush bristle and configuration wear, pullout, and rotor coating wear. The results suggest that sharp changes in the pressure profiles were not well reflected in bristle tip configuration patterns or wear. Also, positive-to-negative changes in axial pressure gradients appeared to have little effect on the backing plates. Although the brushes had similar porosities, they had very different unpacked arrays. This difference could explain the departure of experimental data from computational fluid dynamics flow predictions for well-packed arrays at higher pressure drops. The rotor wear led to “car track” scars (upper and lower wear bands) with a whipped surface between the bands. Those bands may have resulted from bristle stiffening at the fence and gap plates during alternate portions of the rotor cycle. Within the bristle response range the wear surface reflected the pressure distribution effect on bristle motion. No sacrificial metallurgical data were taken. The bristles did wear, with correspondingly more wear on the ID brush configurations than on the OD configurations; the complexity in constructing the ID brush was a factor.
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38

Rogowski, Krzysztof, Martin Otto Laver Hansen, and Galih Bangga. "Performance Analysis of a H-Darrieus Wind Turbine for a Series of 4-Digit NACA Airfoils." Energies 13, no. 12 (2020): 3196. http://dx.doi.org/10.3390/en13123196.

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The purpose of this paper is to estimate the H-Darrieus wind turbine aerodynamic performance, aerodynamic blade loads, and velocity profiles downstream behind the rotor. The wind turbine model is based on the rotor designed by McDonnell Aircraft Company. The model proposed here consists of three fixed straight blades; in the future, this model is planned to be developed with controlled blades. The study was conducted using the unsteady Reynolds averaged Navier–Stokes (URANS) approach with the k-ω shear stress transport (SST) turbulence model. The numerical two-dimensional model was verified using two other independent aerodynamic approaches: a vortex model and the extended version of the computational fluid dynamics (CFD) code FLOWer. All utilized numerical codes gave similar result of the instantaneous aerodynamic blade loads. In addition, steady-state calculations for the applied airfoils were also made using the same numerical model as for the vertical axis wind turbine (VAWT) to obtain lift and drag coefficients. The obtained values of lift and drag force coefficients, for a Reynolds number of 2.9 million, agree with the predictions of the experiment and XFOIL over a wide range of angle of attack. A maximum rotor power coefficient of 0.5 is obtained, which makes this impeller attractive from the point of view of further research. Research has shown that, if this rotor were to work with fixed blades, it is recommended to use the NACA 1418 airfoil instead of the original NACA 0018.
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39

Tezcan, Mehmet Murat, Asim Gökhan Yetgin, Ali Ihsan Canakoglu, Bariş Cevher, Mustafa Turan, and Murat Ayaz. "Investigation of the effects of the equivalent circuit parameters on induction motor torque using three different equivalent circuit models." MATEC Web of Conferences 157 (2018): 01019. http://dx.doi.org/10.1051/matecconf/201815701019.

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In this study, the most vital characteristic properties of induction motor, motor starting, maximum and nominal torque are analyzed for what are affected. For the analysis of torque, L type, T type and IEEE 112 equivalent circuit model is employed. Torque change is investigated with the help of codes developed in MATLAB to be used in electrical machines course. First, the slip-moment characteristic curve of the induction motor is divided into three working zones and it was determined which equivalent circuit model gave the best results in these study zones. Later, such parameters as stator and rotor resistance, stator and rotor reactance, magnetization reactance, core resistance and slip are researched for how torque values are affected from. The obtained values for each of the three equivalent circuit models are given and compared with experimental results. 50 HP squirrel cage induction motor parameters are used in analysis. In the analysis, the most influential parameters on the starting torque are found as rotor resistance and stator and rotor reactance. Change of other parameters’ impact ratio depending upon right proportion and inverse proportion is observed. When nominal torque variations are investigated, again rotor resistance is the most influential parameter and by selecting proper factor effecting rotor resistance during design, the result of acquiring desired rotor resistance is obtained. When the maximum torque variations are examined, it appears that the stator and rotor reactance values are effective. Starting, maximum and nominal torque expressions change with square of voltage alters the effect on them a lot. Therefore, triangle or star connection importance arises during machine design.
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40

Ha, Yoon-Jin, Ji-Yong Park, and Seung-Ho Shin. "Numerical Study of Non-Linear Dynamic Behavior of an Asymmetric Rotor for Wave Energy Converter in Regular Waves." Processes 9, no. 8 (2021): 1477. http://dx.doi.org/10.3390/pr9081477.

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This study conducted a numerical investigation on the non-linear motion problems between a Salter duck-type rotor and large waves using CFD simulations. Regular waves of five different wave heights were generated. First, the linear motion of the rotor from the CFD simulation was verified by comparing it with the existing experimental and frequency domain analysis results. Then, a series of CFD simulations were performed to investigate the non-linear motions of the rotor. In the case of a lower wave height, the CFD simulation results were in good agreement with the experimental and frequency domain analysis results. However, as the wave height increased, the resonance periods were different in each other. In addition, the magnitudes of normalized pitch motions by the wave heights decreased as the wave heights increased. To investigate the aforementioned phenomena, the pitch motion equation was examined using separate CFD simulations. The results showed that changing the restoring moments induced changes in the maximum pitch motions and magnitudes of the normalized pitch motions. In the case of a higher wave height, non-linear phenomena and the changing restoring moments induced non-linear motion.
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41

Povinelli, L. A. "Assessment of Three-Dimensional Inviscid Codes and Loss Calculations for Turbine Aerodynamic Computations." Journal of Engineering for Gas Turbines and Power 107, no. 2 (1985): 265–75. http://dx.doi.org/10.1115/1.3239706.

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An assessment of several three-dimensional inviscid turbine aerodynamic computer codes and loss models used at the NASA Lewis Research Center is presented. Five flow situations are examined, for which both experimental data and computational results are available. The five flows form a basis for the evalution of the computational procedures. It was concluded that stator flows may be calculated with a high degree of accuracy, whereas rotor flow fields are less accurately determined. Exploitation of contouring, leaning, bowing, and sweeping will require a three-dimensional viscous analysis technique.
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42

Karadimas, G. "Design of High-Performance Fans Using Advanced Aerodynamics Codes." Journal of Turbomachinery 110, no. 4 (1988): 419–25. http://dx.doi.org/10.1115/1.3262214.

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In the recent past, the performance of transonic fans has been significantly improved. In addition, through the extensive use of advanced aerodynamic computation codes, the development time required has been considerably reduced. Methods used range from the definition of airfoils in quasi-three-dimensional flow with boundary layer optimization to the analysis of three-dimensional inviscid flow for stage operation at the design point and in off-design conditions. Such a set of methods was used to design the fan blade of the CFM56-5 engine to a very high performance level. This paper will discuss the optimization of rotor and stator airfoils, the assessment of off-design performance, and the operational stability of this fan. A detailed comparison of full-size component test data with computation results shows the validity of these methods and also identifies those areas where research is still required.
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43

Shafik, M., B. Nyathi, and S. Fekkai. "Computer Simulation and Modelling of 3D Travelling Wave Ultrasonic Motor Using a Flexural Vibration Ring Transducer." Applied Mechanics and Materials 307 (February 2013): 31–41. http://dx.doi.org/10.4028/www.scientific.net/amm.307.31.

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This paper presents a 3D piezoelectric ultrasonic motor using a single Flexural Vibration Ring Transducer. The motor consists of three main parts, the rotor, the stator and the housing unit. The stator is a piezoelectric transducer ring made from PZT S42 material. Three steel rods and a magnet were designed to support the rotor. The rotor is a sphere of metal that rests on the stator intersecting at the tips of the steel rods and the magnet. The housing unit is made of Perspex, a transparent thermoplastic material. Longitudinal and bending vibration modes, of oscillating structures are superimposed in the motor, generating elliptical micro motions at the driving tips. Pressing the rotor against the stator tips the micro motions are converted into a 3D rotational motion, via the friction between the tips of the three rods and the rotor. The motor structures, working principles, design and finite element analysis are discussed in this paper. A prototype of the motor was fabricated and its characteristics measured. Experimental tests show typical speed of movement equal to 35 revolutions per minute, a resolution of less than 5μm and maximum load of 3.5 Newton.
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44

Tokuda, N., T. Sakurai, and T. Teraoku. "Sloshing Analysis Method Using Existing FEM Structural Analysis Code." Journal of Pressure Vessel Technology 117, no. 3 (1995): 268–72. http://dx.doi.org/10.1115/1.2842122.

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A fluid analysis method using an analogy relating the pressure wave equation of fluid to elasticity equations is applied to sloshing analysis, where existing FEM structural analysis codes are available. It is seen from theoretical consideration that the present method is equivalent to the classical FEM formulation of linear sloshing analysis. The numerical analyses of liquid sloshing in a rigid cubic tank and of vibration of tubulous fluid under gravitational force are performed by using the present method. The results are shown to be in excellent agreement with the theoretical values.
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45

Hoyniak, D., and S. Fleeter. "Forced Response Analysis of an Aerodynamically Detuned Supersonic Turbomachine Rotor." Journal of Vibration and Acoustics 108, no. 2 (1986): 117–24. http://dx.doi.org/10.1115/1.3269311.

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High-performance aircraft engine fan and compressor blades are vulnerable to aerodynamically forced vibrations generated by inlet flow distortions due to wakes from upstream blade and vane rows, atmospheric gusts, and maldistributions in inlet ducts. In this paper, an analysis is developed to predict the flow-induced forced response behavior of an aerodynamically detuned rotor operating in a supersonic flow with a subsonic axial component. The aerodynamic detuning is achieved by alternating the circumferential spacing of adjacent rotor blades. The total unsteady aerodynamic loading acting on the blading, due to the convection of the transverse gust past the airfoil cascade and the resulting motion of the cascade, is developed in terms of influence coefficients. This analysis is then utilized to investigate the effect of aerodynamic detuning on the forced response characteristics of a 12-bladed rotor, with Verdon’s Cascade B flow geometry as a uniformly spaced baseline configuration. The results of this study indicate that for forward traveling wave gust excitations, aerodynamic detuning is generally very beneficial, resulting in significantly decreased maximum amplitude blade responses for many interblade phase angles.
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46

Banerjee, Arundhuti, Tanusree Chakraborty, and Vasant Matsagar. "Stochastic Dynamic Analysis of an Offshore Wind Turbine Considering Frequency-Dependent Soil–Structure Interaction Parameters." International Journal of Structural Stability and Dynamics 18, no. 06 (2018): 1850086. http://dx.doi.org/10.1142/s0219455418500864.

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This study investigates the dynamic response of a 5[Formula: see text]MW offshore wind turbine with monopile foundation subjected to wind and wave actions under parked condition. It includes dynamic interaction between the monopile and the underlying soil subjected to stochastic wind and wave loading. The offshore wind turbine tower has been modeled using the finite element software ANSYS 14 as a line structure and it comprises a rotor blade system, a nacelle, and a flexible tower under parked condition. The mass of the rotor, blade, and nacelle are lumped at the top of the tower for simplicity. Stochastic wind and wave loadings are simulated using the Kaimal spectrum and the Pierson–Moskowitz spectrum correlating wind and wave forces, respectively. The soil–structure interaction (SSI) effect at the foundation level is taken into consideration by including rotational as well as lateral spring constants derived from Wolf’s double cone model for embedded foundations. The results are studied in the frequency domain for both wind and wave loadings in the form of power spectral density functions, which show that the response of the structure depends not only on the external forces but also on the soil–structure interaction effect. Under very soft soil conditions, the displacement response is amplified to a very high value under wind loading when compared with that under wave loading at lower frequencies. Incorporation of soil–structure interaction also modified the peak value of displacement and its subsequent frequency when compared with that for the fixed base structure which does not consider soil–structure interaction.
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47

Angina, Andrea, Andrea Steri, Stefano Stacul, and Diego Lo Presti. "Free-Field Seismic Response Analysis." International Journal of Geotechnical Earthquake Engineering 9, no. 1 (2018): 1–21. http://dx.doi.org/10.4018/ijgee.2018010101.

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This paper shows the results of free-field seismic response analyses (SRA), that were performed for the subsoil conditions of Piazza dei Miracoli in Pisa. The site investigation and in particular the shear wave velocity profile is extended down to 120 m below the ground level. One-dimensional SRA were carried out by using three computer codes, EERA, STRATA and ONDA. The first two codes perform the analyses in the frequency domain considering a linear-equivalent soil model. ONDA analyses the problem in the time domain assuming a true non-linear soil behaviour. In particular, the Ramberg-Osgood constitutive model, coupled with a modified Masing criterion was assumed. The computed elastic response spectra were compared to those prescribed by the Italian Building Code, which represents the Italian implementation of Eurocodes. Some details concerning the response spectra prescribed by Italian Building Code are also given.
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48

Ha, Yoon-Jin, Ji Yong Park, Seung Ho Shin, and Yoon Hyeok Bae. "Evaluation of Generating Power in Low Wave Height for Asymmetric Rotor using Frequency Domain Analysis." Journal of the Korean Society for Marine Environment & Energy 22, no. 4 (2019): 253–61. http://dx.doi.org/10.7846/jkosmee.2019.22.4.253.

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49

Yoo, Chang-Sun, Am Cho, Bum-Jin Park, and Young-Shin Kang. "Sea Wave Modeling Analysis and Simulation for Shipboard Landing of Tilt Rotor Unmanned Aerial Vehicle." Journal of the Korean Society for Aeronautical & Space Sciences 42, no. 9 (2014): 731–38. http://dx.doi.org/10.5139/jksas.2014.42.9.731.

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50

Szidarovszky, Tamás, Csaba Fábri, and Attila G. Császár. "The role of axis embedding on rigid rotor decomposition analysis of variational rovibrational wave functions." Journal of Chemical Physics 136, no. 17 (2012): 174112. http://dx.doi.org/10.1063/1.4707463.

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