Littérature scientifique sur le sujet « Structural mistuning »
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Articles de revues sur le sujet "Structural mistuning"
Wei, S. T., et C. Pierre. « Localization Phenomena in Mistuned Assemblies with Cyclic Symmetry Part I : Free Vibrations ». Journal of Vibration and Acoustics 110, no 4 (1 octobre 1988) : 429–38. http://dx.doi.org/10.1115/1.3269547.
Texte intégralFu, Zhi Zhong, et Yan Rong Wang. « Mistuning and Structural Coupling Effects on Flutter of Turbomachinery Blades ». Applied Mechanics and Materials 482 (décembre 2013) : 311–14. http://dx.doi.org/10.4028/www.scientific.net/amm.482.311.
Texte intégralKenyon, J. A., J. H. Griffin et D. M. Feiner. « Maximum Bladed Disk Forced Response From Distortion of a Structural Mode ». Journal of Turbomachinery 125, no 2 (1 avril 2003) : 352–63. http://dx.doi.org/10.1115/1.1540118.
Texte intégralKenyon, J. A., et 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 (27 décembre 2002) : 113–20. http://dx.doi.org/10.1115/1.1498269.
Texte intégralMignolet, Marc P., Wei Hu et 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.
Texte intégralMignolet, Marc P., Wei Hu et 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.
Texte intégralKan, Xuanen, et 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 (20 décembre 2022) : 1031–37. http://dx.doi.org/10.5194/ms-13-1031-2022.
Texte intégralLalanne, Bernard. « Perturbations Methods in Structural Dynamics and Applications to Cyclic Symmetric Domains ». Journal of Engineering for Gas Turbines and Power 127, no 3 (13 décembre 2004) : 654–62. http://dx.doi.org/10.1115/1.1924430.
Texte intégralKenyon, J. A., et J. H. Griffin. « Experimental Demonstration of Maximum Mistuned Bladed Disk Forced Response ». Journal of Turbomachinery 125, no 4 (1 octobre 2003) : 673–81. http://dx.doi.org/10.1115/1.1624847.
Texte intégralLiu, Zhanhe, Jinlou Quan, Jingyuan Yang, Dan Su et 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 (octobre 2018) : 856–64. http://dx.doi.org/10.1051/jnwpu/20183650856.
Texte intégralThèses sur le sujet "Structural mistuning"
POURKIAEE, SEYYEDMEHRDAD. « Modelli ed esperimenti per la dinamica non lineare di dischi palettati con mistuning e contatti con attrito ». Doctoral thesis, Politecnico di Torino, 2020. http://hdl.handle.net/11583/2861352.
Texte intégralSternchüss, Arnaud. « Multi-level parametric reduced models of rotating bladed disk assemblies ». Phd thesis, Ecole Centrale Paris, 2009. http://tel.archives-ouvertes.fr/tel-00366252.
Texte intégralSchneider, Alexandra Patrizia. « Aerodynamic and aeroelastic investigation of a composite fan for ultra-high-bypass-ratio aircraft engines ». Electronic Thesis or Diss., Ecully, Ecole centrale de Lyon, 2024. http://www.theses.fr/2024ECDL0018.
Texte intégralModern low-speed Ultra-High Bypass Ratio (UHBR) fans operate predominantly on the flat part of the compression characteristic, have shorter intake lengths, and employ flexible, lightweight, composite blades. These changes promote the evolution of different types of instabilities with multi-physical interactions such as convective non-synchronous vibration (NSV). To enable further technological ad-vancements, experimental benchmark data on representative geometries required. Within this con-text, the European project CATANA was initiated at Ecole Centrale de Lyon. The open-test-case fan stage ECL5 was designed, following industrial guidelines, and tested experimentally on the facility ECL-B3. This thesis presents the experimental results of the CATANA project. The experimental investiga-tion of the ECL5 reference configuration shows that all design goals have been reached. The machine is operational in a wide range and aerodynamic performance at design condition is exactly coincident with the numerical prediction. In contrast, instability mechanisms are more complex than predicted by the employed numerical methods. Through application of synchronized multi-physical instrumenta-tion, the involved complex fluid-structure interaction is resolved. The analysis of the influence of in-flow conditions and geometrical and structural system symmetry allows to identify the sensitivity of aerodynamic and structural characteristics and the behavior close to the stability limit. The investiga-tion of a second rotor configuration featuring structural mistuning highlights the importance of geo-metrical blade-to-blade variations. They cause an asymmetry of the aerodynamic field at the blade tip and suppress coherently propagating aerodynamic disturbances resulting in a delayed onset of NSV. The results presented in this thesis provide a comprehensive multi-physical characterization of the ECL5 fan stage and serve as a benchmark data set for the validation of numerical simula-tions
Mayorca, María Angélica. « Development and Validation of a Numerical Tool for theAeromechanical Design of Turbomachinery ». Licentiate thesis, KTH, Energy Technology, 2010. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-11992.
Texte intégralIn aeromechanical design one of the major rules is to operate under High Cyclic Fatigue (HCF) margins and away from flutter. The level of dynamic excitations and risk of HCF can be estimated by performing forced response analyses from blade row interaction forces or Low Engine Order (LEO) excitation mechanisms. On the other hand, flutter stability prediction can be assessed by calculation of aerodynamic damping forces due to blade motion. In order to include these analyses as regular practices in an industrial aeromechanical design process, interaction between the fields of fluid and structural dynamics must be established in a rather simple yet accurate manner. Effects such as aerodynamic and structural mistuning should also be taken into account where parametric and probabilistic studies take an important role.
The present work presents the development and validation of a numerical tool for aeromechanical design. The tool aims to integrate in a standard and simple manner regular aeromechanical analysis such as forced response analysis and aerodynamic damping analysis of bladed disks.
Mistuning influence on forced response and aerodynamic damping is assessed by implementing existing model order reduction techniques in order to decrease the computational effort and assess results in an industrially applicable time frame. The synthesis program solves the interaction of structure and fluid from existing Finite Element Modeling (FEM) and Computational Fluid Dynamics (CFD) solvers inputs by including a mapping program which establishes the fluid and structure mesh compatibility. Blade row interaction harmonic forces and/or blade motion aerodynamic damping forces are inputs from unsteady fluid dynamic solvers whereas the geometry, mass and stiffness matrices of a blade alone or bladed disk sector are inputs from finite element solvers. Structural and aerodynamic damping is also considered.
Structural mistuning is assessed by importing different sectors and any combinations of the full disk model can be achieved by using Reduced Order Model (ROM) techniques. Aerodynamic mistuning data can also be imported and its effects on the forced response and stability assessed. The tool is developed in such a way to allow iterative analysis in a simple manner, being possible to realize aerodynamically and structurally coupled analyses of industrial bladed disks. A new method for performing aerodynamic coupled forced response and stability analyses considering the interaction of different mode families has also been implemented. The method is based on the determination of the aerodynamic matrices by means of least square approximations and is here referred as the Multimode Least Square (MLS) method.
The present work includes the program description and its applicability is assessed on a high pressure ratio transonic compressor blade and on a simple blisk.
Turbopower
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Mayorca, María Angélica. « Development and Validation of a Numerical Tool for the Aeromechanical Design of Turbomachinery ». Licentiate thesis, KTH, Kraft- och värmeteknologi, 2010. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-11992.
Texte intégralQC 20110324
Turbopower
AROMA
Livres sur le sujet "Structural mistuning"
Afolabi, Dare. Effects of mistuning and matrix structure on the topology of frequency response curves. Cleveland, Ohio : Lewis Research Center, 1989.
Trouver le texte intégralCenter, Lewis Research, dir. Effects of mistuning and matrix structure on the topology of frequency response curves. Cleveland, Ohio : Lewis Research Center, 1989.
Trouver le texte intégralChapitres de livres sur le sujet "Structural mistuning"
Kahl, G. « Structural Mistuning and Aerodynamic Coupling in Turbomachinery Bladings ». Dans Unsteady Aerodynamics and Aeroelasticity of Turbomachines, 335–46. Dordrecht : Springer Netherlands, 1998. http://dx.doi.org/10.1007/978-94-011-5040-8_22.
Texte intégralChan, Y. J., et D. J. Ewins. « The application of robust design strategies on managing the uncertainty and variability issues of the blade mistuning vibration problem ». Dans IUTAM Symposium on the Vibration Analysis of Structures with Uncertainties, 443–56. Dordrecht : Springer Netherlands, 2011. http://dx.doi.org/10.1007/978-94-007-0289-9_32.
Texte intégralChen, G., et J. Hou. « Effects of mistuning patterns on forced response for an integrally bladed disk ». Dans Recent Advances in Structural Integrity Analysis - Proceedings of the International Congress (APCF/SIF-2014), 193–97. Elsevier, 2014. http://dx.doi.org/10.1533/9780081002254.193.
Texte intégralActes de conférences sur le sujet "Structural mistuning"
KAZA, KRISHNA, ORAL MEHMED, MARC WILLIAMS et LARRY MOSS. « Analytical and experimental investigation of mistuning in propfan flutter ». Dans 28th Structures, Structural Dynamics and Materials Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-739.
Texte intégralSHAH, ASHWIN, V. NAGPAL et C. CHAMIS. « Probabilistic analysis of bladed turbine disks and the effect of mistuning ». Dans 31st Structures, Structural Dynamics and Materials Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-1097.
Texte intégralPhan, Hien, et Li He. « Phasing Structural and Aerodynamic Mistuning For Leveraging Aeroelastic Performance ». Dans ASME Turbo Expo 2022 : Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/gt2022-82168.
Texte intégralPhan, H. M., et L. He. « ANALYSIS OF STRUCTURALLY AND AERODYNAMICALLY MISTUNED OSCILLATING BLADEROW USING FULLY-COUPLED METHOD ». Dans GPPS Xi'an21. GPPS, 2022. http://dx.doi.org/10.33737/gpps21-tc-330.
Texte intégralStapelfeldt, Sina, et Christoph Brandstetter. « Suppression of Non-Synchronous-Vibration Through Intentional Aerodynamic and Structural Mistuning ». Dans ASME Turbo Expo 2021 : Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2021. http://dx.doi.org/10.1115/gt2021-59659.
Texte intégralMadden, Andrew, Matthew Castanier et Bogdan Epureanu. « Mistuning Identification of Blisks at Higher Frequencies ». Dans 50th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-2458.
Texte intégralWHALEY, P., et J. MACBAIN. « Effects of mistuning on the forced vibration of bladed disks in subsonic flow ». Dans 26th Structures, Structural Dynamics, and Materials Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-760.
Texte intégralLian, Bo, Xiaocheng Zhu et Zhaohui Du. « Mistuning Effects on Aero-Elastic Stability of Civil Transonic Fan Blades ». Dans ASME Turbo Expo 2022 : Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/gt2022-80613.
Texte intégralGillaugh, Daniel, Alexander Kaszynski, Jeffrey M. Brown, David A. Johnston et Joseph C. Slater. « Accurate Strain Gage Limits Through Geometry Mistuning Modeling ». Dans 58th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virginia : American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-0865.
Texte intégralSladojevic´, I., E. P. Petrov, M. Imregun et A. I. Sayma. « Forced Response Variation of Aerodynamically and Structurally Mistuned Turbo-Machinery Rotors ». Dans ASME Turbo Expo 2006 : Power for Land, Sea, and Air. ASMEDC, 2006. http://dx.doi.org/10.1115/gt2006-90948.
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