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Journal articles on the topic 'Model rotor'

Author: Grafiati

Published: 28 May 2022

Last updated: 18 July 2025

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1

Peters, Nicholas, Christopher Silva, and John Ekaterinaris. "A data-driven reduced-order model for rotor optimization." Wind Energy Science 8, no. 7 (2023): 1201–23. http://dx.doi.org/10.5194/wes-8-1201-2023.

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Abstract. For rotor design applications, such as wind turbine rotors or urban air mobility (UAM) rotorcraft and flying-car design, there is a significant challenge in quickly and accurately modeling rotors operating in complex, turbulent flow fields. One potential path for deriving reasonably accurate but low-cost rotor performance predictions is available through the application of data-driven surrogate modeling. In this study, an initial investigation is undertaken to apply a proper orthogonal decomposition (POD)-based reduced-order model (ROM) for predicting rotor distributed loads. The POD

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2

Muhammed Ameen, Yahya, and Jaafar Khalaf Ali. "Flexible rotor balancing without trial runs using experimentally tuned FE based rotor model." Basrah journal of engineering science 21, no. 1 (2021): 20–26. http://dx.doi.org/10.33971/bjes.21.1.4.

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A method based on experimentally calibrated rotor model is proposed in this work for unbalance identification of flexible rotors without trial runs. Influence coefficient balancing method especially when applied to flexible rotors is disadvantaged by its low efficiency and lengthy procedure, whilst the proposed method has the advantage of being efficient, applicable to multi-operating spin speeds and do not need trial runs. An accurate model for the rotor and its supports based on rotordynamics and finite elements analysis combined with experimental modal analysis, is produced to identify the

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3

Aa. Madsen, H. "Exploration of an analytical, linear two-dimensional actuator disc model as basis for a general rotor induction model." Journal of Physics: Conference Series 2767, no. 2 (2024): 022043. http://dx.doi.org/10.1088/1742-6596/2767/2/022043.

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Abstract The state of the art BEM based aerodynamic and aeroelastic modelling is challenged by effects rising from the upscaling of wind turbine rotors such as non-planar rotor shapes due to increased blade bending and large instantaneous load variations over the rotor disc due to inflow turbulence and shear. This calls for new engineering aerodynamic modelling approaches. We present such a new approach by exploration of the implementation of an analytical 2-D actuator disc (AD) model called 2D l for use as a rotor induction model. The overall approach is to use superposition of an elementary

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4

Muszynska, A. "Improvements in Lightly Loaded Rotor/Bearing and Rotor/Seal Models." Journal of Vibration and Acoustics 110, no. 2 (1988): 129–36. http://dx.doi.org/10.1115/1.3269489.

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A model for lightly loaded steadily rotating shaft/bearing/seal systems is proposed in this paper. The model is based on modal characteristics for the rotor, and rotational characteristics for the fluid dynamic forces generated in bearings and/or seals. The fluid average circumferential velocity ratio as a nonlinear function of shaft eccentricity represents a key factor in the model. The model is extremely useful for rotor stability analysis. The model adequacy was proved for one and two lateral mode models of rotors.

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5

Buranarote, Jirarote, Yutaka Hara, Masaru Furukawa, and Yoshifumi Jodai. "Method to Predict Outputs of Two-Dimensional VAWT Rotors by Using Wake Model Mimicking the CFD-Created Flow Field." Energies 15, no. 14 (2022): 5200. http://dx.doi.org/10.3390/en15145200.

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Recently, wind farms consisting of clusters of closely spaced vertical-axis wind turbines (VAWTs) have attracted the interest of many people. In this study, a method using a wake model to predict the flow field and the output power of each rotor in a VAWT cluster is proposed. The method uses the information obtained by the preliminary computational fluid dynamics (CFD) targeting an isolated single two-dimensional (2D) VAWT rotor and a few layouts of the paired 2D rotors. In the method, the resultant rotor and flow conditions are determined so as to satisfy the momentum balance in the main wind

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6

Wang, Jinhong, Zhenping Li, Hongguang Li, Wendi Zhang, and Ke Bao. "Dynamics analysis of the nonlinear rotor system with Geislinger coupling." Vibroengineering PROCEDIA 49 (May 18, 2023): 73–79. http://dx.doi.org/10.21595/vp.2023.23334.

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Rotor systems with coupling consist of two rotors, rolling bearings, sealing components, and nonlinear coupling. Currently, rotor systems with coupling are widely used in marine engines, aerospace engines, and various vehicle engines. In studies of rotor systems with coupling, the coupling connecting both sides of the rotor are often regarded as a linear stiffness unit. But in actual engineering, the torsional stiffness of the coupling varies with the speed of the system, and the variation of the coupling stiffness will affect the dynamic characteristics of the rotor. Based on the above phenom

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7

Peng, Jifeng. "Effects of Aerodynamic Interactions of Closely-Placed Vertical Axis Wind Turbine Pairs." Energies 11, no. 10 (2018): 2842. http://dx.doi.org/10.3390/en11102842.

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In this study, a numerical model was developed to study the effects of aerodynamic interactions between a pair of counter-rotating vertical axis wind turbines (VAWTs) in close proximity. In this model, the rotor rotation is not prescribed as a constant as in most other studies, but is determined by the moment of inertia and the total torque of the rotor, including the aerodynamic torque, generator torque, and a torque representing friction. This model enables study of the behavior of the rotor under an arbitrary ambient wind profile. The model was applied to an isolated rotor with five straigh

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8

Sun, Chuanzhi, Ruirui Li, Ze Chen, et al. "Research on Vibration Suppression Method Based on Coaxial Stacking Measurement." Mathematics 9, no. 12 (2021): 1438. http://dx.doi.org/10.3390/math9121438.

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A dynamic analysis model of the unbalanced vibration response of a single-rotor system is established to study the corresponding mechanism of the unbalanced excitation force and vibration response caused by the deviation of the rotor mass centroid in this paper, and finally to achieve the combined rotor vibration suppression. First, the installation of multi-stage rotors during vibration was studied, and the rotor mass centroid transfer model in the rotating coordinate system was established to obtain the unbalanced excitation force vectors of the rotors at all levels based on the traditional

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9

Kong, Yong-Boon, J. V. R. Prasad, Lakshmi N. Sankar, and Chengjian He. "Finite State Inflow Flow Model for Coaxial Rotor Configuration." Journal of the American Helicopter Society 65, no. 3 (2020): 1–11. http://dx.doi.org/10.4050/jahs.65.032002.

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An analytical coaxial rotor inflow model has been developed from potential flow theory using the pressure potential superposition approach. The coaxial rotor pressure potential superposition inflow model (PPSIM) is formulated in statespace form with structure similar to the Peters–He model, except that additional off-diagonal blocks are included in the apparent mass (M-matrix) and influence coefficient matrices (L-matrix). These off-diagonal blocks take into account mutual interference effects present in a coaxial rotor system by relating the rotor's inflows due to other rotor's pressure loadi

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10

Khaimovich, A. I., M. A. Bolotov, and E. Yu Pechenina. "Model of virtual balancing of rigid rotors." VESTNIK of Samara University. Aerospace and Mechanical Engineering 21, no. 1 (2022): 99–109. http://dx.doi.org/10.18287/2541-7533-2022-21-1-99-109.

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Rotor imbalances have a significant impact on the level of their vibration and reliability. Reduction of rotor imbalances is achieved through static and dynamic balancing that we propose to accomplish by virtual balancing of rigid rotors in two stages. At the first stage mutual orientation of the rotor parts is calculated to compensate their imbalances and couple unbalance. At the second stage the values of the masses and angular coordinates of two correction weights that allow eliminating the residual imbalance of the rotor are determined. The correction weights are placed in two balancing pl

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11

Wang, Nanfei, Hongzhi Xu, and Dongxiang Jiang. "Dynamic Model and Fault Feature Research of Dual-Rotor System with Bearing Pedestal Looseness." Mathematical Problems in Engineering 2016 (2016): 1–18. http://dx.doi.org/10.1155/2016/3817405.

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The paper presents a finite element model of dual-rotor system with pedestal looseness stemming from loosened bolts. Dynamic model including bearing pedestal looseness is established based on the dual-rotor test rig. Three-degree-of-freedom (DOF) planar rigid motion of loose bearing pedestal is fully considered and collision recovery coefficient is also introduced in the model. Based on the Timoshenko beam elements, using the finite element method, rigid body kinematics, and the Newmark-βalgorithm for numerical simulation, dynamic characteristics of the inner and outer rotors and the bearing p

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12

Povarov, Sergii. "Determination of the aerodynamic characteristics of the tiltrotor with the wingtip-mounted coaxial rotors." MECHANICS OF GYROSCOPIC SYSTEMS, no. 40 (December 26, 2021): 108–16. http://dx.doi.org/10.20535/0203-3771402020248778.

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The article describes the study of rotor-to-wing aerodynamic interaction for the wingtip-mounted coaxial rotors configuration of the tiltrotor aircraft. The influence of the rotor slipstreams on lift-to-drag ratio characteristic was determined. Obtained results were compared with similar characteristics of the equivalent in thrust conventional single rotor slipstreams impact. Using the computational aerodynamics methods (panel-vortex method) the flow around the tiltrotor model with the wingtip-mounted single and coaxial rotors has been simulated. A study of the basic model configur

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Povarov, Sergey. "Comparison of aerodynamic characteristics of convertible models with single and coaxial schemes of propellers." MECHANICS OF GYROSCOPIC SYSTEMS, no. 39 (May 20, 2020): 96–105. http://dx.doi.org/10.20535/0203-3771392020229110.

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The article describes the study of rotor-to-wing aerodynamic interaction for the wingtip-mounted coaxial rotors configuration of the tiltrotor aircraft. The influence of the rotor slipstreams on lift-to-drag ratio characteristic was determined. Obtained results were compared with similar characteristics of the equivalent in thrust conventional single rotor slipstreams impact. Using the computational aerodynamics methods (panel-vortex method) the flow around the tiltrotor model with the wingtip-mounted single and coaxial rotors has been simulated. A study of the basic model configur

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14

Zaytsev, Nikolay, Denis Zaytsev, Andrey Makarov, and Dmitriy Mineev. "NUMERICAL SIMULATION OF THE DYNAMICS OF A FLEXIBLE ROTOR WITH TWO BALL AUTO-BALANCERS." Perm National Research Polytechnic University Aerospace Engineering Bulletin, no. 62 (2020): 31–44. http://dx.doi.org/10.15593/2224-9982/2020.62.04.

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Ball auto-balancing devices can to compensate changes of unbalance "on the move" only for rotors operating at supercritical speeds. For automatic balancing of such rotors, classified as flexible rotors, several auto-balancers located in different cross sections of the shaft are necessary. This makes it necessary to account bending fluctuations on studies of dynamics of the rotor with auto-balancers, that is especially important in the design of the real rotors. In view of the complexity of experimental studies of such rotors in the article the method of direct numerical simulation of the dynam

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15

Yang, S.-C. "A mathematical model of the rotor profile of the single-screw compressor." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 216, no. 3 (2002): 343–51. http://dx.doi.org/10.1243/0954406021525052.

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This paper presents a method for determining the basic profile of a single-screw compressor including a gate rotor and a screw rotor. The inverse envelope concept for determining the cutting-edge curve of the gate rotor is presented. Based on this concept, the required cutter for machining the screw rotor can be obtained by an envelope of the one-parameter family of obtained screw rotors. The obtained screw rotor is an envelope of the family of gate rotor surfaces. Let the obtained envelope of the one-parameter family of gate rotor surfaces become the generating surface. The inverse envelope c

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16

Dayhoum, Abdallah, Alejandro Ramirez-Serrano, and Robert J. Martinuzzi. "Analytical Modeling of Shrouded Rotors in Hover with Experimental and Computational Validation." Actuators 14, no. 3 (2025): 138. https://doi.org/10.3390/act14030138.

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Rotors have been utilized for aircraft propulsion since the dawn of aviation, but their performance can degrade significantly if not properly designed. This study focuses on developing an accurate design tool and model validation for shrouded rotors. An experimental test rig was designed and manufactured to measure the rotor thrust and total thrust separately as well as the rotor torque. A key aspect was to account for the impact of a test rig on experimental results using computational simulations for the shrouded rotor configuration with and without the test rig. The findings indicate that t

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17

Zhong, Shun, Suxia Zhang, Jie Yang, and Yanan Zhang. "Correlation Analysis and Its Application on an Asymmetry Rotor Structure with Overhang." Applied Sciences 11, no. 23 (2021): 11501. http://dx.doi.org/10.3390/app112311501.

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Overhung rotors are widely used in the industrial field. However, compared with normal structure rotors, the prediction and control of overhung rotors cannot achieve good performance. The work aims to investigate the dynamical behaviours of an overhung rotor by means of correlation analysis, and find its possible application. In this work, based on a real type of rotor, the dynamic model of the rotor with overhang is established by means of the finite element method. Simulation of the dynamic model with different input positions and support stiffnesses is conducted. Based on the methodology of

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18

Grachev, I. A., E. V. Kudashov, M. A. Bolotov, and N. D. Pronichev. "Model for evaluating the end runouts of a rotor with parallel connections of parts." VESTNIK of Samara University. Aerospace and Mechanical Engineering 20, no. 2 (2021): 83–96. http://dx.doi.org/10.18287/2541-7533-2021-20-2-83-96.

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The existing methods for calculating the assembly dimensional chains of aircraft engine rotors are analyzed. The factors that have a significant impact on the reliability of the calculation of the controlled assembly parameters of the product are identified. One of these factors is the existence of parallel connections of parts in the rotor. In the drum disk rotors, parallel rotor connections are formed by mating their parts along several end surfaces in the axial direction. A mathematical model is proposed that allows taking into account the parallel connections of the rotor parts. The form o

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19

Tucker, V. A. "Using a Collision Model to Design Safer Wind Turbine Rotors for Birds." Journal of Solar Energy Engineering 118, no. 4 (1996): 263–69. http://dx.doi.org/10.1115/1.2871791.

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A mathematical model for collisions between birds and propellor-type turbine rotors identifies the variables that can be manipulated to reduce the probability that birds will collide with the rotor. This study defines a safety index—the “clearance power density”—that allows rotors of different sizes and designs to be compared in terms of the amount of wind energy converted to electrical energy per bird collision. The collision model accounts for variations in wind speed during the year and shows that for model rotors with simple, one-dimensional blades, the safety index increases in proportion

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20

Varatharajoo, Renuganth, Faizal Mustapha, Dayang Laila Abang Abdul Majid, Rizal Zahari, and Ralph Kahle. "Critical Speeds for Carbon/Epoxy Composite Rotors in Spacecraft Energy Storage Applications." Key Engineering Materials 471-472 (February 2011): 37–42. http://dx.doi.org/10.4028/www.scientific.net/kem.471-472.37.

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A numerical investigation to optimize the carbon/epoxy multi layer composite rotor is performed for the spacecraft energy storage application. A high-speed double and triple layer rotor design is proposed and different composite materials are tested to achieve the most suitable recipe. First, analytical rotor evaluation was performed in order to establish a reliable numerical composite rotor model. Subsequently, finite element analysis is employed in order to optimize the double and triple layer composite rotors. Then, the modal analysis was carried out to determine the rotor natural frequenci

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21

Ren, Jiakan, and Hong Zhang. "Critical speed analysis on high-speed foil bearing rotor of fuel cell air compressor." Journal of Physics: Conference Series 3043, no. 1 (2025): 012034. https://doi.org/10.1088/1742-6596/3043/1/012034.

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Abstract Based on the characteristic analysis of dynamic pressure gas bearing, the reliability analysis of high-speed rotors of fuel cell air compressors is carried out in this paper, which is of great significance for the study of the safety of automotive fuel cell systems. The calculation method of rotor critical speed is introduced, and its key role in the reliability analysis of the rotor system is analyzed. The dynamic pressure gas bearing used in the rotor system is calculated and analyzed, and its stiffness and damping changes with the speed are obtained. Based on the calculated bearing

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22

Idris, Muhammad, Zakie Anugia, and Donny Mustika. "DEVELOPMENT OF FINITE ELEMENT ANALYSIS PROGRAM FOR ROTORDYNAMIC PREDICTION OF SINGLE AND MULTI DISK ROTOR MODEL." Indonesian Journal of Engineering and Science 3, no. 3 (2022): 001–13. http://dx.doi.org/10.51630/ijes.v3i3.61.

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The rotating equipment is a crucial part of system performance reliability. Vibration, as a characteristic of an oscillating body, is a fundamental parameter to determine the dynamic behaviour of the rotor system. The dynamic characteristics include natural frequency, critical speed, mode shape, and vibration response. This paper discussed the application of rotordynamics analysis as a tool to numerically predict the dynamic behaviour of a rotor system. The aim is to determine a rotor system's natural frequency and critical speed by a finite element analysis (FEA) program. The selected method

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23

Fletcher, T. M., and R. E. Brown. "Modelling the interaction of helicopter main rotor and tail rotor wakes." Aeronautical Journal 111, no. 1124 (2007): 637–43. http://dx.doi.org/10.1017/s0001924000004814.

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Abstract The mutual interaction between the main rotor and tail rotor wakes is central to some of the most problematic dynamic phenomena experienced by helicopters. Yet achieving the ability to model the growth and propagation of helicopter rotor wakes with sufficient realism to capture the details of this interaction has been a significant challenge to rotorcraft aerodynamicists for many decades. A novel computational fluid dynamics code tailored specifically for rotorcraft applications, the vorticity transport model, has been used to simulate the interaction of the rotors of a helicopter wit

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24

Dayhoum, Abdallah, Mohamed Etewa, Alejandro Ramirez-Serrano, and Robert Martinuzzi. "Enhancing VTOL Performance: Shrouded Rotor BLDC Motor Model and Validation." Journal of Physics: Conference Series 2784, no. 1 (2024): 012004. http://dx.doi.org/10.1088/1742-6596/2784/1/012004.

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Abstract One prominent area of current research interest, driven by a multitude of factors and considerations, centers around drone technology. A primary challenge currently faced in the realm of small-scale Unmanned Aerial Vehicles (UAVs) is the increasing demand for increased power coupled with the constraint of limited flight duration provided by available battery technology. These vehicles fall into two overarching categories based on the presence or absence of shrouding around their rotor(s). Shrouded rotors play a pivotal role in augmenting aerodynamic performance by enhancing thrust whi

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25

Hayami, H., Y. Senoo, Y. I. Hyun, and M. Yamaguchi. "Effects of Tip Clearance of Nozzle Vanes on Performance of Radial Turbine Rotor." Journal of Turbomachinery 112, no. 1 (1990): 58–63. http://dx.doi.org/10.1115/1.2927421.

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In radial turbines with variable nozzles, the flow downstream of the nozzles could be distorted by the leakage flow through the tip clearance of the upstream nozzle vanes. To investigate the effects of flow distortion on the performance of turbine rotors, two rotors with different numbers of blades were tested for three types of distorted velocity distribution at the rotor inlet. In the case of the 20-blade rotor with moderate blade loading, the flow distortion at the rotor inlet had a negligible effect on the rotor characteristics, and the measured data on the turbine performances agreed well

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26

El-Shafei, A., A. S. El-Kabbany, and A. A. Younan. "Rotor Balancing Without Trial Weights." Journal of Engineering for Gas Turbines and Power 126, no. 3 (2004): 604–9. http://dx.doi.org/10.1115/1.1762903.

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The traditional balancing methods using trial or calibration weights are quite effective, yet too many trials may result in a lengthy balancing process. It had been suggested in the literature that it is possible to balance flexible rotors without the use of trial weights, if a rotor model is available. A procedure is developed in this paper to balance flexible rotors using complex modes and complex vibration measurements. It is shown that a complex rotor model is essential for the success of the technique. Moreover, careful calibration of the rotor model is the major cornerstone of the proced

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27

Pacholczyk, Michał, and Dariusz Karkosiński. "Parametric Study on a Performance of a Small Counter-Rotating Wind Turbine." Energies 13, no. 15 (2020): 3880. http://dx.doi.org/10.3390/en13153880.

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A small Counter-Rotating Wind Turbine (CRWT) has been proposed and its performance has been investigated numerically. Results of a parametric study have been presented in this paper. As parameters, the axial distance between rotors and a tip speed ratio of each rotor have been selected. Performance parameters have been compared with reference to a Single Rotor Wind Turbine (SRWT). Simulations were carried out with Computational Fluids Dynamics (CFD) solver and a Large Eddy Scale approach to model turbulences. An Actuator Line Model has been chosen to represent rotors in the computational domai

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28

Lee, Yu-Been, and Jae-Sang Park. "Hover Performance Analyses of Coaxial Co-Rotating Rotors for eVTOL Aircraft." Aerospace 9, no. 3 (2022): 152. http://dx.doi.org/10.3390/aerospace9030152.

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Hover performance analyses of coaxial co-rotating rotors (or stacked rotors), which can be used as lifting rotors for electric VTOL (eVTOL) aircraft, are conducted here. In this study, the rotorcraft comprehensive analysis code, CAMRAD II, is used with the general free-wake model. The generic coaxial co-rotating rotor without the blade taper and built-in twist is considered as the baseline rotor model, and the rotor is trimmed to match a prescribed rotor thrust value. The hover performance, including the rotor power and Figure of Merit (FM), is investigated for various index angles, axial spac

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29

Tan, J., Y. Sun, and G. N. Barakos. "Unsteady loads for coaxial rotors in forward flight computed using a vortex particle method." Aeronautical Journal 122, no. 1251 (2018): 693–714. http://dx.doi.org/10.1017/aer.2018.8.

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ABSTRACTRecent advances in coaxial rotor design have shown benefits of this configuration. Nevertheless, issues related to rotor-head drag, aerodynamic performance, wake interference, and vibration should also be considered. Simulating the unsteady aerodynamic loads for a coaxial rotor, including the aerodynamic interactions between rotors and rotor blades, is an essential part of analysing their vibration characteristics. In this article, an unsteady aerodynamic analysis based on a vortex particle method is presented. In this method, a reversed-flow model for the retreating side of the coaxia

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30

Yang, S.-C. "A mathematical model of a cc-type single-screw compressor." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 218, no. 4 (2004): 437–48. http://dx.doi.org/10.1177/095440620421800408.

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In this paper, a method is proposed for determining a basic profile of a cc-type single-screw compressor including the gate rotor and the screw rotor. The cc-type has a cylindrical screw and two cylindrical gate rotors. Based on this method, a mathematical model of the meshing principles of a cc-type screw rotor meshed with a gate rotor, that has either straight edge teeth or conical teeth, is presented. The inverse envelope concept is used to determine the cutting-edge curve of a gate rotor. Based on this concept, the required cutter for machining a cc-type screw rotor can be obtained by the

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31

Huang, Yao-Tien, Ying-Chieh Liu, Kun-Nan Chen, and Yueh-Mei Lai. "Structural Optimization of Vented Brake Rotors with a Fully Parameterized Model." Applied Sciences 12, no. 4 (2022): 2184. http://dx.doi.org/10.3390/app12042184.

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Vented brake rotors used in an automobile behave similarly to centrifugal fans, drawing cool air from the inboard side, passing it through the disc vents, and exhausting it from the periphery. A vented brake rotor with a better heat dispersing ability is often superior to a solid rotor, in both thermal performance and brake efficiency. In this research, a fully parameterized model for a ventilated brake rotor is created using the ANSYS Parametric Design Language, to uniquely define the rotor’s geometry. With this parameterized model, two structural optimization cases are studied in this paper.

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Yoshida, Shigeo, Haruto Fuchiwaki, and Koji Matsuoka. "Development of Individual Rotor Mutual Induction (IRMI) Method for Coaxial Counter-Rotating Rotor." Applied Sciences 14, no. 11 (2024): 4782. http://dx.doi.org/10.3390/app14114782.

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A coaxial counter-rotating rotor (CCRR), which has two rotors rotating in the opposite directions on the same axis, is seen as a promising technology for low-cost floating tidal current/ocean current power generation using single-point mooring, as the torques of the front and rear rotors are cancelled. In the evaluation and design of such turbines, there is a need for an accurate analysis method with a low computational load that considers the strong mutual induction between the two rotors placed close together. An individual rotor mutual induction (IRMI) method was developed in this study, ai

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33

Hathout, J. P., A. El-Shafei, and R. Youssef. "Active Control of Multi-Mode Rotor-Bearing Systems Using HSFDs." Journal of Tribology 119, no. 1 (1997): 49–56. http://dx.doi.org/10.1115/1.2832479.

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This paper summarizes the modeling and control of hybrid squeeze film dampers (HSFDs) for active control of vibration of rotors exhibiting multiple modes. In a recent paper (El-Shafei and Hathout, 1994), it was shown that the automatically controlled HSFD based on feedback on rotor speed can be a very efficient device for active control of rotor vibration. It was shown that this closed-loop, on-off control strategy results in a much improved behavior of the rotor system. The previous investigation was performed on a Jeffcott rotor model. The model was simple and fluid inertia effects were not

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34

Wang, Nanfei, Dongxiang Jiang, and Hongzhi Xu. "Dynamic characteristics analysis of a dual-rotor system with inter-shaft bearing." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 3 (2017): 1147–58. http://dx.doi.org/10.1177/0954410017748969.

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The dual-rotor structure is susceptible to vibration, causing the malfunction of the entire operating system. In order to avoid the resonance during operation, it is significant and necessary to conduct modal analysis of such rotors. The dynamic analysis of the full dual-rotor system under operating conditions is also necessary to study dynamic characteristics of the rotating system. In this paper, one-dimension Timoshenko beam-type model, including the effects of gyroscopic moments, rotary inertias, bending and shear deformations, and three-dimension model for dual-rotor system with inter-sha

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Zheng, Nan, Mo-li Chen, Gui-Huo Luo, and Zhi-Feng Ye. "Dynamic Behavior Analysis of Intermediate Bearing-Squeeze Film Dampers-Rotor System under Constant Maneuvering Overload." Shock and Vibration 2021 (April 30, 2021): 1–24. http://dx.doi.org/10.1155/2021/5512409.

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Under the flight maneuvering of an aircraft, the maneuvering load on the rotor is generated, which may induce the change of dynamic behavior of aeroengine rotor system. To study the influence on the rotor dynamic behavior of constant maneuvering overload, a nonlinear dynamic model of bearing-rotor system under arbitrary maneuver flight conditions is presented by finite element method. The numerical integral method is used to investigate the dynamic characteristics of the rotor model under constant maneuvering overload, and the simulation results are verified by experimental works. Based on thi

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36

Wen, Jiayu, Yanguo Song, Huanjin Wang, and Dong Han. "Numerical Study on Tandem-Rotor Autorotation in Forward Flight." Aerospace 10, no. 1 (2022): 15. http://dx.doi.org/10.3390/aerospace10010015.

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This work presents a systematic approach to analyzing the aerodynamic characteristics of tandem rotor forward autorotation considering rotor-to-rotor interference. The single-rotor computational model trimmed from a generic helicopter flight dynamics analysis program was used as the baseline model. The effectiveness of the baseline model is demonstrated by a comparison with data from wind tunnel tests performed in this work. The rotor disk angle of attack and driven moment distribution obtained by the modified model indicate the fact that the rotor acceleration is primarily caused by the highe

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Ghaisas, Niranjan S., Aditya S. Ghate, and Sanjiva K. Lele. "Effect of tip spacing, thrust coefficient and turbine spacing in multi-rotor wind turbines and farms." Wind Energy Science 5, no. 1 (2020): 51–72. http://dx.doi.org/10.5194/wes-5-51-2020.

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Abstract. Large eddy simulations (LESs) are performed to study the wakes of a multi-rotor wind turbine configuration comprising four identical rotors mounted on a single tower. The multi-rotor turbine wakes are compared to the wake of a conventional turbine comprising a single rotor per tower with the same frontal area, hub height and thrust coefficient. The multi-rotor turbine wakes are found to recover faster, while the turbulence intensity in the wake is smaller, compared to the wake of the conventional turbine. The differences with the wake of a conventional turbine increase as the spacing

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Shahmiri, Farid. "Twin-rotor hover performance examination using overlap tests." Aircraft Engineering and Aerospace Technology 89, no. 1 (2017): 155–63. http://dx.doi.org/10.1108/aeat-02-2015-0032.

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Purpose The aim of this paper was to experimentally examine twin-rotor hover performance for different rotor overlap ratios at practical rotor loading. Design/methodology/approach The methodology was formed based on data measurements for a designed twin-rotor test model and development of hover performance mathematical models. Thus, measurements were made using a central composite test plan, and then mathematical models for thrust power required power loading (PL) and figure of merit (FM) as functions of collective pitch tip speed; rotor overlap ratio was obtained. In the present paper, the te

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Zhang, Yiming, Jiqiang Tang, and Tong Wen. "A Modified Transfer Matrix Method for Modal Analysis of Stepped Rotor Assembly Applied in the Turbomolecular Pump." Shock and Vibration 2022 (February 27, 2022): 1–13. http://dx.doi.org/10.1155/2022/3692081.

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An accurate modal analysis of the stepped rotor assembly is significant in the design process of rotors. The transfer matrix method (TMM) is widely used in the modal analysis of the rotor. However, the influences of the step and the assembling modes are not considered in the traditional TMM. In this paper, a modified transfer matrix method is presented for the modal calculation of the rotor in the turbomolecular pump. The stiffness reduction of stepped segments and the effect of assembled components are considered in this modified method. First of all, the traditional transfer matrix model is

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Zhao, Yingjie, Xiaokai Mu, Jian Liu, Qingchao Sun, Ping Zhou, and Guozhen Fang. "A Decoupling Algorithm-Based Technology for Predicting and Regulating the Unbalance of Aircraft Rotor Assembly Considering Manufacturing Errors." Machines 11, no. 10 (2023): 970. http://dx.doi.org/10.3390/machines11100970.

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Rotor unbalance is the most important factor affecting the dynamic performance of aircraft engines. The existing unbalance prediction and control methods are insufficient for multi-stage rotors. The post-assembly unbalance of rotors in aircraft engines is a critical factor affecting their dynamic performance. In order to predict and reduce the unbalance of multi-stage rotors after assembly, this paper establishes a measurement model for the center-of-mass offset of aircraft engine rotors through decoupled calculations of the unbalance. Furthermore, it constructs an unbalance prediction model u

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Chen, Yue, Jiwen Cui, and Xun Sun. "A Vibration Suppression Method for the Multistage Rotor of an Aero-Engine Based on Assembly Optimization." Machines 9, no. 9 (2021): 189. http://dx.doi.org/10.3390/machines9090189.

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The assembly quality of the multistage rotor is an essential factor affecting its vibration level. The existing optimization methods for the assembly angles of the rotors at each stage can ensure the concentricity and unbalance meet the requirements, but it cannot directly ensure its vibration responses meet the indexes. Therefore, in this study, we first derived the excitation formulas of the geometric and mass eccentricities on the multistage rotor and introduced it into the dynamics model of the multistage rotor system. Then, the coordinate transfer model of the geometric and mass eccentric

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Xiao, Sen, Pingchao Yu, Zihan Jiang, Cun Wang, Jiayu Chen, and Qicheng Zhang. "Nonlinear Modeling and Vibration Response Analysis of a Dual-Rotor System with an Inter-Shaft Graphite Seal." Mathematics 12, no. 3 (2024): 454. http://dx.doi.org/10.3390/math12030454.

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The inter-shaft graphite seal is a common structure in the dual-rotor system, and may generate nonlinear lateral excitation when there is large relative angular motion at the seal position. This paper represents the first attempt to study the nonlinear behaviors of a dual-rotor system with inter-shaft graphite seal excitations. First, an excitation model of the inter-shaft graphite seal is proposed by the analytical method. This model is then introduced into the beam finite element model of a dual rotor system, and the dynamic equations of the whole system are finally obtained. The vibration r

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Dai, Yuting, Linpeng Wang, Chao Yang, and Xintan Zhang. "Dynamic Gust Load Analysis for Rotors." Shock and Vibration 2016 (2016): 1–12. http://dx.doi.org/10.1155/2016/5727028.

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Dynamic load of helicopter rotors due to gust directly affects the structural stress and flight performance for helicopters. Based on a large deflection beam theory, an aeroelastic model for isolated helicopter rotors in the time domain is constructed. The dynamic response and structural load for a rotor under the impulse gust and slope-shape gust are calculated, respectively. First, a nonlinear Euler beam model with 36 degrees-of-freedoms per element is applied to depict the structural dynamics for an isolated rotor. The generalized dynamic wake model and Leishman-Beddoes dynamic stall model

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Barkat, Ibtissem, Abdelouahab Benretem, Fawaz Massouh, Issam Meghlaoui, and Ahlem Chebel. "Modeling and simulation of forces applied to the horizontal axis wind turbine rotors by the vortex method coupled with the method of the blade element." International Journal of Power Electronics and Drive Systems (IJPEDS) 12, no. 1 (2021): 413. http://dx.doi.org/10.11591/ijpeds.v12.i1.pp413-420.

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This article aims to study the forces applied to the rotors of horizontal axis wind turbines. The aerodynamics of a turbine are controlled by the flow around the rotor, or estimate of air charges on the rotor blades under various operating conditions and their relation to the structural dynamics of the rotor are critical for design. One of the major challenges in wind turbine aerodynamics is to predict the forces on the blade as various methods, including blade element moment theory (BEM), the approach that is naturally adapted to the simulation of the aerodynamics of wind turbines and the dyn

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Ibtissem, Barkat, Benretem Abdelouahab, Massouh Fawaz, Meghlaoui Issam, and Chebel Ahlem. "Modeling and simulation of forces applied to the horizontal axis wind turbine rotors by the vortex method coupled with the method of the blade element." International Journal of Power Electronics and Drive System (IJPEDS) 12, no. 1 (2021): 413–20. https://doi.org/10.11591/ijpeds.v12.i1.pp413-420.

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This article aims to study the forces applied to the rotors of horizontal axis wind turbines. The aerodynamics of a turbine are controlled by the flow around the rotor, or estimate of air charges on the rotor blades under various operating conditions and their relation to the structural dynamics of the rotor are critical for design. One of the major challenges in wind turbine aerodynamics is to predict the forces on the blade as various methods, including blade element moment theory (BEM), the approach that is naturally adapted to the simulation of the aerodynamics of wind turbines and the dyn

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Chen, Yue, Jiwen Cui, and Xun Sun. "An Unbalance Optimization Method for a Multi-Stage Rotor Based on an Assembly Error Propagation Model." Applied Sciences 11, no. 2 (2021): 887. http://dx.doi.org/10.3390/app11020887.

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For the assembly of a multi-stage rotor, such as an aero-engine or gas turbine, the parts need to be assembled optimally to avoid excessive unbalance. We propose a method to optimize the unbalance of a multi-stage rotor during assembly. First, we developed an assembly error propagation model for a multi-stage rotor. The alignment process and distribution of the screw holes of the adjacent rotors was considered for the first time. Secondly, we propose a new assembly datum for unbalance optimization to ensure consistency with the actual conditions of a dynamic balance test. Finally, the unbalanc

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Liu, Jingze, Qingguo Fei, Shaoqing Wu, Zhenhuan Tang, Sanfeng Liao, and Dahai Zhang. "An Efficient Dynamic Modeling Technique for a Central Tie Rod Rotor." International Journal of Aerospace Engineering 2021 (June 8, 2021): 1–11. http://dx.doi.org/10.1155/2021/6618828.

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Compared with the three-dimensional rotor model for a central tie rod rotor, an equivalent one-dimensional model can greatly improve the computational efficiency in rotor dynamics analysis with a certain accuracy. However, little research work can be found on improving the modeling accuracy of one-dimensional models using experimental data. In this paper, a one-dimensional discrete mass model considering pretightening force is proposed for central tie rod rotors to achieve the purpose of both efficient and accurate modeling. Experimental testing and three-dimensional model analysis are used as

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Wang, Jun Yu, Dong Mei Ji, Xiu Ping Yao, Jin Yuan Shi, and Yu Yang. "Research on Stress Field of the Steam Turbine Rotor Based on SVM and the Finite Element Analysis." Advanced Materials Research 354-355 (October 2011): 446–53. http://dx.doi.org/10.4028/www.scientific.net/amr.354-355.446.

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A model for on-line calculation of equivalent stresses in steam turbine rotors has been built up based on Support Vector Machine (SVM) neural network and the finite element method. Regarding 125MW steam turbine rotor as an object, SVM method is employed as a tool to train large numbers of date about the equivalent stress of the rotor, which obtained from the finite element method. A model can be gotten after finishing training the data. Equivalent stresses of rotor obtained with finite element and SVM model are compared during cold start. Results show that similar calculation results of equiva

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Park, J. S., and S. N. Jung. "Comprehensive multibody dynamics analysis for rotor aeromechanics predictions in descending flight." Aeronautical Journal 116, no. 1177 (2012): 229–49. http://dx.doi.org/10.1017/s0001924000006813.

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AbstractThis paper studies the rotor aeromechanics in descending flight using a nonlinear flexible multibody dynamic analysis code, DYMORE. A freewake model is included in DYMORE to improve the rotor wake modelling. The wind-tunnel test data of the Higher-harmonic Aeroacoustics Rotor Test (HART) II rotor, with and without higher harmonic pitch control (HHC), and the flight test data of the full-scale utility helicopter rotor in descent are used for the aeromechanics correlation at an advance ratio of 0·15. The blade-vortex interaction (BVI) airloads are reasonably predicted for both the HART I

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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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