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Artykuły w czasopismach na temat „Structural mistuning”

Autor: Grafiati

Data publikacji: 7 września 2024

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1

Wei, S. T., and C. Pierre. "Localization Phenomena in Mistuned Assemblies with Cyclic Symmetry Part I: Free Vibrations." Journal of Vibration and Acoustics 110, no. 4 (1988): 429–38. http://dx.doi.org/10.1115/1.3269547.

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An investigation of the effects of small structural irregularities on the dynamics of nearly periodic structures with cyclic symmetry is presented. The system studied may be regarded as a simple model of a continuously shrouded blade assembly accounting for one structural mode per blade. A key aspect of the approach is the use of perturbation methods that lead to a physical insight into the effects of mistuning. The study shows that the sensitivity to mistuning depends primarily upon the ratio of mistuning strength to coupling strength. For a small mistuning to coupling ratio, the mistuned sys

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2

Fu, Zhi Zhong, and Yan Rong Wang. "Mistuning and Structural Coupling Effects on Flutter of Turbomachinery Blades." Applied Mechanics and Materials 482 (December 2013): 311–14. http://dx.doi.org/10.4028/www.scientific.net/amm.482.311.

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A fast numerical method based on aeroelastic eigenvalue analysis is applied to study the effects of mistuning on the aeroelastic stability of turbomachinery blades in which the structural coupling is included by a simplified method and an influence coefficient method is employed to deal with the unsteady aerodynamic effects. Results show that there exists an optimal mistuning amount at which the system has the best aeroelastic stability. Structural coupling almost has no effects on aeroelastic stability of a tuned system. But the benefit of alternate frequency mistuning to aeroelastic stabilit

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3

Kenyon, J. A., J. H. Griffin, and D. M. Feiner. "Maximum Bladed Disk Forced Response From Distortion of a Structural Mode." Journal of Turbomachinery 125, no. 2 (2003): 352–63. http://dx.doi.org/10.1115/1.1540118.

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A method is presented for obtaining maximum bladed disk forced response from distortion of a structural mode. It is shown that maximum response from mode distortion in a bladed disk occurs when the harmonic components of a distorted mode superimpose in a certain manner, causing localization of the mode and strong response in a particular blade. In addition, it is shown that the response of an intentionally mistuned system with maximum response does not change significantly when small random mistuning is added to the system. A method is described for calculating the structural mistuning necessa

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4

Kenyon, J. A., and J. H. Griffin. "Forced Response of Turbine Engine Bladed Disks and Sensitivity to Harmonic Mistuning." Journal of Engineering for Gas Turbines and Power 125, no. 1 (2002): 113–20. http://dx.doi.org/10.1115/1.1498269.

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The mistuned forced response of turbine engine bladed disks is treated using harmonic perturbations in the properties of a continuous ring. A continuous shear spring is attached to the ring in which the stiffness is allowed to vary along the ring annulus. The modes of such a structure with a single harmonic mistuning pattern are shown to obey the Mathieu equation, which is solved to obtain the natural frequencies and modes of the mistuned system. The forced response of the system is then examined to determine the sensitivity of the system to small mistuning. The model is extended to include mu

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5

Mignolet, Marc P., Wei Hu, and Ioan Jadic. "On the Forced Response of Harmonically and Partially Mistuned Bladed Disks. Part I: Harmonic Mistuning." International Journal of Rotating Machinery 6, no. 1 (2000): 29–41. http://dx.doi.org/10.1155/s1023621x0000004x.

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This series of two papers focuses on the determination and clarification of the characteristics of the forced response of bladed disks that exhibit a mistuning pattern that is either harmonic or partial. Harmonic mistuning refers to single wavelength variations in structural properties along the disk while partial mistuning is associated with blade characteristics that are random in a specific sector and tuned elsewhere. The results of this analysis demonstrate that many features of the response of these simple systems match not only qualitatively but also quantitatively their counterparts on

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6

Mignolet, Marc P., Wei Hu, and Ioan Jadic. "On the Forced Response of Harmonically and Partially Mistuned Bladed Disks. Part II: Partial Mistuning and Applications." International Journal of Rotating Machinery 6, no. 1 (2000): 43–56. http://dx.doi.org/10.1155/s1023621x00000051.

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This series of two papers focuses on the determination and clarification of the characteristics of the forced response of bladed disks that exhibit a mistuning pattern that is either harmonic or partial. Harmonic mistuning refers to single wavelength variations in structural properties along the disk while partial mistuning is associated with blade characteristics that are random in a specific sector and tuned elsewhere. The results of this analysis demonstrate that many features of the response of these simple systems match not only qualitatively but also quantitatively their counterparts on

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7

Kan, Xuanen, and Tuo Xing. "A novel mathematical model for the design of the resonance mechanism of an intentional mistuning bladed disk system." Mechanical Sciences 13, no. 2 (2022): 1031–37. http://dx.doi.org/10.5194/ms-13-1031-2022.

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Abstract. Bladed disk systems with advanced functions are widely used in turbo-machineries. However, there are always deviations in physical dynamic properties between blades and blades due to the tolerance and wear in operation. The deviations will lead to vibration localization, which will result in high cycle fatigue and accelerate the damage of the bladed disk system. Therefore, many intentional mistuning patterns are proposed to overcome this larger local vibration. Previous studies show that intentional mistuning patterns can be used to reduce the vibration localization of the bladed dis

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8

Lalanne, Bernard. "Perturbations Methods in Structural Dynamics and Applications to Cyclic Symmetric Domains." Journal of Engineering for Gas Turbines and Power 127, no. 3 (2004): 654–62. http://dx.doi.org/10.1115/1.1924430.

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The design of components must take into account the irregularities inherent to the manufacturing process. When the structures have close eigenvalues, small mass and stiffness variations or the damping generate strong variations of the eigenmodes: these structures are then not robust. Here, their dynamics has been analyzed by perturbation method, in the dissipative cases and with coupling within a light fluid. A new perturbation method allows first order developments whatever the spectral density may be. Applications to many different vibration problems are presented: aeroelasticity, mode veeri

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9

Kenyon, J. A., and J. H. Griffin. "Experimental Demonstration of Maximum Mistuned Bladed Disk Forced Response." Journal of Turbomachinery 125, no. 4 (2003): 673–81. http://dx.doi.org/10.1115/1.1624847.

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A theory was previously developed for predicting robust maximum forced response in mistuned bladed disks from distortion of a structural mode. This paper describes an experiment to demonstrate the theory. A bladed disk is designed to be sufficiently sensitive to mistuning to obtain maximum response. The maximum amplitude magnification from mistuning is predicted using the theory, 1.918. The bladed disk is intentionally mistuned to obtain the maximum response, and the response to an engine order traveling wave excitation is measured. The measured amplitude magnification is in close agreement wi

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10

Liu, Zhanhe, Jinlou Quan, Jingyuan Yang, Dan Su, and Weiwei Zhang. "A High Efficient Fluid-Structure Interaction Method for Flutter Analysis of Mistuned." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 36, no. 5 (2018): 856–64. http://dx.doi.org/10.1051/jnwpu/20183650856.

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The time cost is very high by direct fluid-structure interaction method for mistuned bladed disk structures, so aerodynamic loads generally are ignored or treated as small perturbations in traditional flutter analysis. In order to analyze the flutter characteristics of mistuned blade rapidly and accurately, this paper presents an efficient fluid-structure interaction method based on aerodynamic reduced order model. system identification technology and two basic assumptions are used to build the unsteady aerodynamic reduced order model. Coupled the structural equations and the aerodynamic model

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11

Beirow, B., A. Kühhorn, F. Figaschewsky, P. Hönisch, T. Giersch, and S. Schrape. "Model update and validation of a mistuned high-pressure compressor blisk." Aeronautical Journal 123, no. 1260 (2019): 230–47. http://dx.doi.org/10.1017/aer.2018.149.

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ABSTRACTIn order to prepare an advanced 4-stage high-pressure compressor rig test campaign, details regarding both accomplishment and analysis of preliminary experiments are provided in this paper. The superior objective of the research project is to contribute to a reliable but simultaneously less conservative design of future high pressure blade integrated disks (blisk). It is planned to achieve trend-setting advances based on a close combination of both numerical and experimental analyses. The analyses are focused on the second rotor of this research compressor, which is the only one being

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12

Basu, P., and J. H. Griffin. "The Effect of Limiting Aerodynamic and Structural Coupling in Models of Mistuned Bladed Disk Vibration." Journal of Vibration and Acoustics 108, no. 2 (1986): 132–39. http://dx.doi.org/10.1115/1.3269313.

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A model has been developed for studying the effect of mistuning on bladed disk vibration. Its unique feature is the extent of aerodynamic and structural interaction which it simulates can be readily varied from full coupling of all blades on the disk to coupling of each blade with only its nearest neighbors. Simulations utilizing the resulting algorithm shows that limited coupling models may be used to predict the statistical distribution of blade amplitudes that characterizes the mistuning effect, which in turn determines stage durability. This approach is used to study the effect of changing

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13

Afolabi, D. "Vibration Amplitudes of Mistuned Blades." Journal of Turbomachinery 110, no. 2 (1988): 251–57. http://dx.doi.org/10.1115/1.3262188.

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Due to the mistuning effect, the nominally identical blades on a rotor are forced to vibrate with greatly unequal amplitudes under certain circumstances. It is, therefore, desirable to have the capability of predicting the highest responding blades so that such blades may be instrumented during engine tests. However, the predictions of various investigators in this regard are apparently inconsistent. Usually, the inconsistency is attributed to differences in mathematical models. By using modal analysis, it is shown that the various results are really not in conflict, but merely reflect the loc

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14

Ibrahim, R. A. "Structural Dynamics with Parameter Uncertainties." Applied Mechanics Reviews 40, no. 3 (1987): 309–28. http://dx.doi.org/10.1115/1.3149532.

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The treatment of structural parameters as random variables has been the subject of structural dynamicists and designers for many years. Several problems have been involved during the last few decades and resulted in new theorems and interesting phenomena. This paper reviews a number of topics pertaining to structural dynamics with parameter uncertainties. These include direct problems such as random eigenvalues and random responses of discrete and continuous systems. The impact of these problems on related areas of interest such as sensitivity of structural performance to parameter variations,

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15

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

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

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16

Bai, Bin, Qi Yang, Guang Wei Zhu, Qi Liang Wu, and Xin ye Li. "Nonproportional Intentionally Mistuned Turbine Blisk Design with Improved Component Modal Synthesis." Shock and Vibration 2021 (January 29, 2021): 1–16. http://dx.doi.org/10.1155/2021/6658694.

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An improved component modal synthesis-based nonproportional mistuning method (ICMS-NPMM) is proposed to investigate mistuned turbine blisks (MTBs) since the high-fidelity finite element models (HFEMs) involve large number of computations, which leads to low calculation efficiency. To reduce degrees of freedom and suppress the flutter of MTB, it is divided into mistuned blade structure and tuned disk structure, and the intentional mistuning is considered. Furthermore, the mistuned parameters, nonproportional mistuning, and complex loads are also considered. Firstly, the basic theory of ICMS-NPM

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17

Wang, Shuai, Chuanxing Bi, Bin Zi, and Changjun Zheng. "Vibration Characteristics of Rotating Mistuned Bladed Disks considering the Coriolis Force, Spin Softening, and Stress Stiffening Effects." Shock and Vibration 2019 (November 12, 2019): 1–22. http://dx.doi.org/10.1155/2019/9714529.

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Bladed disks of engine rotors usually operate at harsh conditions of high rotating speeds, which may lead to nonnegligible rotordynamic effects, including Coriolis force, spin softening, and stress stiffening effects. These effects on the vibration of mistuned bladed disks are seldom discussed in available investigations. In this paper, the vibration characteristics of rotating mistuned bladed disks are addressed by considering these rotordynamic effects. First, finite element (FE) models of bladed disks are used to obtain the governing equations of motion, and an efficient method for getting

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18

Lin, R. M., and T. Y. Ng. "Prediction of mistuning effect of bladed disks using eigensensitivity analysis." Engineering Structures 212 (June 2020): 110416. http://dx.doi.org/10.1016/j.engstruct.2020.110416.

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19

Rogge, Timo, Ricarda Berger, Linus Pohle, Raimund Rolfes, and Jörg Wallaschek. "Efficient structural analysis of gas turbine blades." Aircraft Engineering and Aerospace Technology 90, no. 9 (2018): 1305–16. http://dx.doi.org/10.1108/aeat-05-2016-0085.

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Purpose The purpose of this study a fast procedure for the structural analysis of gas turbine blades in aircraft engines. In this connection, investigations on the behavior of gas turbine blades concentrate on the analysis and evaluation of starting dynamics and fatigue strength. Besides, the influence of structural mistuning on the vibration characteristics of the single blade is analyzed and discussed. Design/methodology/approach A basic computation cycle is generated from a flight profile to describe the operating history of the gas turbine blade properly. Within an approximation approach f

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20

Repetckii, Oleg, and Dinh Cuong Hoang. "Numerical Analysis for Optimization of the Lifetime Characteristics of Radial Wheels Turbomachines by Introducing the Intentional Mistuning Parameters." System Analysis & Mathematical Modeling 5, no. 2 (2023): 192–204. http://dx.doi.org/10.17150/2713-1734.2023.5(2).192-204.

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Due to manufacturing tolerances, small deviations in the mass of the blade always introduce changes in the geometry and structural properties of the design. Changed geometry and parameters of the blade significantly affect the characteristics of the wheel and the performance of the design of the entire turbomachine. These deviations break the cyclic symmetry of the turbine wheel and are called system mistuning. Generally, the tighter the manufacturing tolerance, the smaller the blade mass deviation. However, if the manufacturing tolerances are tighter, then the manufacturing cost becomes highe

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21

Cha, D., and A. Sinha. "Statistics of Response of a Mistuned Bladed Disk Assembly Subjected to White Noise and Narrow Band Excitation." Journal of Engineering for Gas Turbines and Power 121, no. 4 (1999): 710–17. http://dx.doi.org/10.1115/1.2818531.

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This paper deals with the statistics of the response of a mistuned bladed disk assembly subjected to random excitation. Analytical techniques are developed to compute this statistics for two types of random excitation: white noise and narrow band. The validity of the analytical methods has been established by comparison with the results from numerical simulations. The sensitivities of the response to mistuning have been examined as a function of the width of the frequency band of the random excitation, the dominant frequency of the random excitation and the structural coupling between adjacent

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22

Mignolet, M. P., and W. Hu. "Direct Prediction of the Effects of Mistuning on the Forced Response of Bladed Disks." Journal of Engineering for Gas Turbines and Power 120, no. 3 (1998): 626–34. http://dx.doi.org/10.1115/1.2818192.

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In this paper, a novel approach to determine reliable estimates of the moments of the steady-state resonant response of a randomly mistuned bladed disk is presented, and the use of these moments to accurately predict the corresponding distribution of the amplitude of blade vibration is described. The estimation of the moments of the response is accomplished first by relying on a “joint cumulant closure” strategy that expresses higher order moments in terms of lower order ones. A simple modeling of the error terms of these approximations is also suggested that allows the determination of an imp

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23

Xu, Kunpeng, Wei Sun, and Xianfei Yan. "A structural damping identification technique for coatings on blisks based on improved component mode mistuning model." Thin-Walled Structures 151 (June 2020): 106737. http://dx.doi.org/10.1016/j.tws.2020.106737.

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24

Yang, M. T., and J. H. Griffin. "A Reduced-Order Model of Mistuning Using a Subset of Nominal System Modes." Journal of Engineering for Gas Turbines and Power 123, no. 4 (1999): 893–900. http://dx.doi.org/10.1115/1.1385197.

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Reduced-order models have been reported in the literature that can be used to predict the harmonic response of mistuned bladed disks. It has been shown that in many cases they exhibit structural fidelity comparable to a finite element analysis of the full bladed disk system while offering a significant improvement in computational efficiency. In these models the blades and disk are treated as distinct substructures. This paper presents a new, simpler approach for developing reduced-order models in which the modes of the mistuned system are represented in terms of a subset of nominal system mod

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25

Zhou, Biao, Jingchao Zhao, and Teresa Maria Berruti. "Exploration of blade detuning tests for mistuning identification of blisks." Mechanical Systems and Signal Processing 175 (August 2022): 109118. http://dx.doi.org/10.1016/j.ymssp.2022.109118.

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26

Figaschewsky, F., A. Kühhorn, B. Beirow, T. Giersch, and S. Schrape. "Analysis of mistuned forced response in an axial high-pressure compressor rig with focus on Tyler–Sofrin modes." Aeronautical Journal 123, no. 1261 (2019): 356–77. http://dx.doi.org/10.1017/aer.2018.163.

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ABSTRACTThis paper aims at contributing to a better understanding of the effect of Tyler–Sofrin Modes (TSMs) on forced vibration responses by analysing a 4.5-stage research axial compressor rig. The first part starts with a brief review of the involved physical mechanisms and necessary prerequisites for the generation of TSMs in multistage engines. This review is supported by unsteady CFD simulations of a quasi 2D section of the studied engine. It is shown that the amplitude increasing effect due to mistuning can be further amplified by the presence of TSMs. Furthermore, the sensitivity with r

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27

Pichot, F., D. Laxalde, J. J. Sinou, F. Thouverez, and J. P. Lombard. "Mistuning identification for industrial blisks based on the best achievable eigenvector." Computers & Structures 84, no. 29-30 (2006): 2033–49. http://dx.doi.org/10.1016/j.compstruc.2006.08.022.

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28

Mignolet, M. P., A. J. Rivas-Guerra, and J. P. Delor. "Identification of Mistuning Characteristics of Bladed Disks From Free Response Data—Part I." Journal of Engineering for Gas Turbines and Power 123, no. 2 (1999): 395–403. http://dx.doi.org/10.1115/1.1338949.

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The focus of the present two-part investigation is on the estimation of the dynamic properties, i.e., masses, stiffnesses, natural frequencies, mode shapes and their statistical distributions, of turbomachine blades to be used in the accurate prediction of the forced response of mistuned bladed disks. As input to this process, it is assumed that the lowest natural frequencies of the blades alone have been experimentally measured, for example, in a broach block test. Since the number of measurements is always less than the number of unknowns, this problem is indeterminate in nature. In this fir

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29

Rivas-Guerra, A. J., M. P. Mignolet, and J. P. Delor. "Identification of Mistuning Characteristics of Bladed Disks From Free Response Data— Part II." Journal of Engineering for Gas Turbines and Power 123, no. 2 (1999): 404–11. http://dx.doi.org/10.1115/1.1338950.

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The focus of the present two-part investigation is on the estimation of the dynamic properties, i.e., masses, stiffnesses, natural frequencies, mode shapes and their statistical distributions, of turbomachine blades to be used in the accurate prediction of the forced response of mistuned bladed disks. As input to this process, it is assumed that the lowest natural frequencies of the blades alone have been experimentally measured, for example in a broach block test. Since the number of measurements is always less than the number of unknowns, this problem is indeterminate in nature. In this seco

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30

Píštěk, Václav, Pavel Kučera, Oleksij Fomin, Alyona Lovska, and Aleš Prokop. "Acoustic Identification of Turbocharger Impeller Mistuning—A New Tool for Low Emission Engine Development." Applied Sciences 10, no. 18 (2020): 6394. http://dx.doi.org/10.3390/app10186394.

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At present, exhaust gas turbochargers not only form the basis for the economical operation of petrol, diesel or gas engines of all power categories, but also have an irreplaceable role on reducing their emissions. In order to reduce emissions from internal combustion engines, various systems are being developed, all of which have a turbocharger as an important component. Demands on turbocharger system durability and reliability keep growing, which requires the application of increasingly advanced computational and experimental methods at the development beginning of these systems. The design o

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31

Moyroud, F., T. Fransson, and G. Jacquet-Richardet. "A Comparison of Two Finite Element Reduction Techniques for Mistuned Bladed Disks." Journal of Engineering for Gas Turbines and Power 124, no. 4 (2002): 942–52. http://dx.doi.org/10.1115/1.1415741.

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The high performance bladed disks used in today’s turbomachines must meet strict standards in terms of aeroelastic stability and resonant response level. One structural characteristic that can significantly impact on both these areas is that of bladed disk mistuning. To predict the effects of mistuning, computational efficient methods are much needed to make free-vibration and forced-response analyses of full assembly finite element (FE) models feasible in both research and industrial environments. Due to the size and complexity of typical industrial bladed disk models, one must resort to robu

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32

Tan, Yuanqiu, Chaoping Zang, and E. P. Petrov. "Mistuning sensitivity and optimization for bladed disks using high-fidelity models." Mechanical Systems and Signal Processing 124 (June 2019): 502–23. http://dx.doi.org/10.1016/j.ymssp.2019.02.002.

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Liu, Honghao, Wei Sun, Dongxu Du, Xiaofeng Liu, and Hongwei Ma. "Nonlinear vibration of mistuning bolted composite plates considering stick-slip-separation characteristics." International Journal of Mechanical Sciences 245 (May 2023): 108126. http://dx.doi.org/10.1016/j.ijmecsci.2023.108126.

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34

Xu, Kunpeng, Wei Sun, and Junnan Gao. "Mistuning identification and model updating of coating blisk based on modal test." Mechanical Systems and Signal Processing 121 (April 2019): 299–321. http://dx.doi.org/10.1016/j.ymssp.2018.11.029.

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35

Sall, A. C., F. Thouverez, L. Blanc, and P. Jean. "Stochastic Behaviour of Mistuned Stator Vane Sectors: An Industrial Application." Shock and Vibration 19, no. 5 (2012): 1041–50. http://dx.doi.org/10.1155/2012/798610.

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Stator vanes which are found in axial compressors are subject to vibratory fatigue. Their division into monoblock sectors makes the prediction of their vibratory behaviour difficult by deterministic methods due to the loss of the cyclic symmetry properties and also to a high sensitivity to mistuning. The purpose is to present a robust calculation strategy based on a stochastic modelisation of the structure. The methodology has been developed first on a simplified model and then applied to an industrial case. Polynomial chaos based results are in good agreement with reference Monte Carlo simula

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36

Yan, Xianfei, Dongxu Du, Honghao Liu, Kunpeng Xu, and Wei Sun. "Nonlinear vibration analysis of coated blisks in the presence of stiffness mistuning identification." Mechanical Systems and Signal Processing 165 (February 2022): 108338. http://dx.doi.org/10.1016/j.ymssp.2021.108338.

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Baek, Seunghun, and Bogdan Epureanu. "Damping mistuning effects on the amplification factor and statistical investigation of vane packet." Mechanical Systems and Signal Processing 120 (April 2019): 117–32. http://dx.doi.org/10.1016/j.ymssp.2018.10.011.

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38

Zhou, Biao, and Teresa Maria Berruti. "A novel model reduction approach for blisks with blend repairs and small mistuning." Mechanical Systems and Signal Processing 195 (July 2023): 110308. http://dx.doi.org/10.1016/j.ymssp.2023.110308.

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39

Yan, Xianfei, Wei Sun, Jinpeng Su, and Qiang Zhang. "Optimization-based vibration suppression method of deterministic blisks by nonlinear coatings with mistuning identification." Structures 53 (July 2023): 986–99. http://dx.doi.org/10.1016/j.istruc.2023.04.121.

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40

Schwerdt, Lukas, Niklas Maroldt, Lars Panning-von Scheidt, Joerg Wallaschek, and Joerg Seume. "An improved reduced order model for bladed disks including multistage aeroelastic and structural coupling." Journal of the Global Power and Propulsion Society 7 (April 25, 2023): 140–52. http://dx.doi.org/10.33737/jgpps/161707.

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To assess the influence of mistuning on the vibration amplitudes of turbomachinery rotors, reduced order models (ROMs) are widely used. A variety of methods are available for single-stage configurations and mostly aeroelastic effects can be taken into account. More recent research focusses on extending these methods to include multiple stages. However, due to the significantly increased computational effort of the aeroelastic simulations when adding more stages to the models, these ROMs are rarely applied with the inclusion of multistage aeroelastic effects. It is therefore desirable to develo

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Tacher, Anthony, Fabrice Thouverez, and Jason Armand. "Modelling and analysis of a bladed drum subject to the Coriolis and mistuning effects." International Journal of Mechanical Sciences 218 (March 2022): 106994. http://dx.doi.org/10.1016/j.ijmecsci.2021.106994.

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Fitzner, Colin, Bogdan I. Epureanu, and Sergio Filippi. "Nodal energy weighted transformation: A mistuning projection and its application to FLADE™ turbines." Mechanical Systems and Signal Processing 42, no. 1-2 (2014): 167–80. http://dx.doi.org/10.1016/j.ymssp.2013.08.027.

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Xu, Kunpeng, Xianfei Yan, Dalu Xu, Dongxu Du, and Wei Sun. "Detection of blade substrate crack parameters of hard-coated blisk based on mistuning identification technology." Mechanical Systems and Signal Processing 165 (February 2022): 108381. http://dx.doi.org/10.1016/j.ymssp.2021.108381.

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Yan, Xianfei, Wei Sun, Kunpeng Xu, and Dongxu Du. "Modelling method and mistuning amplification analysis of the forced response for coated blisks in the presence of coatings-material nonlinearity." Thin-Walled Structures 154 (September 2020): 106850. http://dx.doi.org/10.1016/j.tws.2020.106850.

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Wang, Weimin, Dongfang Hu, Qihang Li, and Xulong Zhang. "An improved non-contact dynamic stress measurement method for turbomachinery rotating blades based on fundamental mistuning model." Mechanical Systems and Signal Processing 144 (October 2020): 106851. http://dx.doi.org/10.1016/j.ymssp.2020.106851.

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Xiao, Congzhen, Zhenhong Wu, Kai Chen, Yi Tang, and Yalin Yan. "Development of a Water Supplement System for a Tuned Liquid Damper under Excitation." Buildings 13, no. 5 (2023): 1115. http://dx.doi.org/10.3390/buildings13051115.

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Integrating existing liquid storage and supply tanks in buildings with tuned liquid dampers (TLDs) are significant for reducing the effective cost of TLDs. However, existing water supplement devices for fire-suppression liquid tanks may overfill with water, which leads to TLD mistuning. To overcome this problem, a passive liquid control system named TLD with a stable replenishment sub-tank system (TLD-SRS) is proposed. The system, which consists of an additional sub-tank connected to the main tank and a floating ball, replenishes liquid in the TLD automatically. The system can avoid vibration

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Xu, Hailong, Zhongsheng Chen, Yongmin Yang, Limin Tao, and Xuefeng Chen. "Effects of Crack on Vibration Characteristics of Mistuned Rotated Blades." Shock and Vibration 2017 (2017): 1–18. http://dx.doi.org/10.1155/2017/1785759.

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Rotated blades are key mechanical components in turbine and high cycle fatigues often induce blade cracks. Meanwhile, mistuning is inevitable in rotated blades, which often makes it much difficult to detect cracks. In order to solve this problem, it is important and necessary to study effects of crack on vibration characteristics of mistuned rotated blades (MRBs). Firstly, a lumped-parameter model is established based on coupled multiple blades, where mistuned stiffness with normal distribution is introduced. Next, a breathing crack model is adopted and eigenvalue analysis is used in coupled l

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Fan, Zhenfang, Hongkun Li, Jiannan Dong, Daitong Wei, Hongwei Cao, and Yugang Chen. "An improved mistuning identification and dynamic strain prediction method for rotating blades with application of blade tip timing technology." Mechanical Systems and Signal Processing 184 (February 2023): 109684. http://dx.doi.org/10.1016/j.ymssp.2022.109684.

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Hu, Dongfang, Weimin Wang, Xulong Zhang, and Kang Chen. "On-line real-time mistuning identification and model calibration method for rotating blisks based on blade tip timing (BTT)." Mechanical Systems and Signal Processing 147 (January 2021): 107074. http://dx.doi.org/10.1016/j.ymssp.2020.107074.

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Jay, R. L., and D. W. Burns. "Characteristics of the Diametral Resonant Response of a Shrouded Fan Under a Prescribed Distortion." Journal of Vibration and Acoustics 108, no. 2 (1986): 125–31. http://dx.doi.org/10.1115/1.3269312.

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A comprehensive controlled study of the resonant vibratory structural response of a shrouded fan blade/disk due to known excitation was performed. A full circumferential definition of the inlet velocity field was obtained at five radial locations for three axial spacings and for four unique patterns of distortion and three mass flow rates. Harmonic analyses of the velocity patterns were used to establish a gust perturbation velocity normal to the blade chord. From these spanwise perturbation velocities, a normalized force parameter was established. In-vacuum, nonrotating testing of the fan ass

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