Auswahl der wissenschaftlichen Literatur zum Thema „Structural mistuning“
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Zeitschriftenartikel zum Thema "Structural mistuning"
Wei, S. T., und C. Pierre. „Localization Phenomena in Mistuned Assemblies with Cyclic Symmetry Part I: Free Vibrations“. Journal of Vibration and Acoustics 110, Nr. 4 (01.10.1988): 429–38. http://dx.doi.org/10.1115/1.3269547.
Der volle Inhalt der QuelleFu, Zhi Zhong, und Yan Rong Wang. „Mistuning and Structural Coupling Effects on Flutter of Turbomachinery Blades“. Applied Mechanics and Materials 482 (Dezember 2013): 311–14. http://dx.doi.org/10.4028/www.scientific.net/amm.482.311.
Der volle Inhalt der QuelleKenyon, J. A., J. H. Griffin und D. M. Feiner. „Maximum Bladed Disk Forced Response From Distortion of a Structural Mode“. Journal of Turbomachinery 125, Nr. 2 (01.04.2003): 352–63. http://dx.doi.org/10.1115/1.1540118.
Der volle Inhalt der QuelleKenyon, J. A., und J. H. Griffin. „Forced Response of Turbine Engine Bladed Disks and Sensitivity to Harmonic Mistuning“. Journal of Engineering for Gas Turbines and Power 125, Nr. 1 (27.12.2002): 113–20. http://dx.doi.org/10.1115/1.1498269.
Der volle Inhalt der QuelleMignolet, Marc P., Wei Hu und Ioan Jadic. „On the Forced Response of Harmonically and Partially Mistuned Bladed Disks. Part I: Harmonic Mistuning“. International Journal of Rotating Machinery 6, Nr. 1 (2000): 29–41. http://dx.doi.org/10.1155/s1023621x0000004x.
Der volle Inhalt der QuelleMignolet, Marc P., Wei Hu und 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, Nr. 1 (2000): 43–56. http://dx.doi.org/10.1155/s1023621x00000051.
Der volle Inhalt der QuelleKan, Xuanen, und Tuo Xing. „A novel mathematical model for the design of the resonance mechanism of an intentional mistuning bladed disk system“. Mechanical Sciences 13, Nr. 2 (20.12.2022): 1031–37. http://dx.doi.org/10.5194/ms-13-1031-2022.
Der volle Inhalt der QuelleLalanne, Bernard. „Perturbations Methods in Structural Dynamics and Applications to Cyclic Symmetric Domains“. Journal of Engineering for Gas Turbines and Power 127, Nr. 3 (13.12.2004): 654–62. http://dx.doi.org/10.1115/1.1924430.
Der volle Inhalt der QuelleKenyon, J. A., und J. H. Griffin. „Experimental Demonstration of Maximum Mistuned Bladed Disk Forced Response“. Journal of Turbomachinery 125, Nr. 4 (01.10.2003): 673–81. http://dx.doi.org/10.1115/1.1624847.
Der volle Inhalt der QuelleLiu, Zhanhe, Jinlou Quan, Jingyuan Yang, Dan Su und Weiwei Zhang. „A High Efficient Fluid-Structure Interaction Method for Flutter Analysis of Mistuned“. Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 36, Nr. 5 (Oktober 2018): 856–64. http://dx.doi.org/10.1051/jnwpu/20183650856.
Der volle Inhalt der QuelleDissertationen zum Thema "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.
Der volle Inhalt der QuelleSternchüss, Arnaud. „Multi-level parametric reduced models of rotating bladed disk assemblies“. Phd thesis, Ecole Centrale Paris, 2009. http://tel.archives-ouvertes.fr/tel-00366252.
Der volle Inhalt der QuelleSchneider, 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.
Der volle Inhalt der QuelleModern 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.
Der volle Inhalt der QuelleIn 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.
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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.
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Bücher zum Thema "Structural mistuning"
Afolabi, Dare. Effects of mistuning and matrix structure on the topology of frequency response curves. Cleveland, Ohio: Lewis Research Center, 1989.
Den vollen Inhalt der Quelle findenCenter, Lewis Research, Hrsg. Effects of mistuning and matrix structure on the topology of frequency response curves. Cleveland, Ohio: Lewis Research Center, 1989.
Den vollen Inhalt der Quelle findenBuchteile zum Thema "Structural mistuning"
Kahl, G. „Structural Mistuning and Aerodynamic Coupling in Turbomachinery Bladings“. In Unsteady Aerodynamics and Aeroelasticity of Turbomachines, 335–46. Dordrecht: Springer Netherlands, 1998. http://dx.doi.org/10.1007/978-94-011-5040-8_22.
Der volle Inhalt der QuelleChan, Y. J., und D. J. Ewins. „The application of robust design strategies on managing the uncertainty and variability issues of the blade mistuning vibration problem“. In 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.
Der volle Inhalt der QuelleChen, G., und J. Hou. „Effects of mistuning patterns on forced response for an integrally bladed disk“. In 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.
Der volle Inhalt der QuelleKonferenzberichte zum Thema "Structural mistuning"
KAZA, KRISHNA, ORAL MEHMED, MARC WILLIAMS und LARRY MOSS. „Analytical and experimental investigation of mistuning in propfan flutter“. In 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.
Der volle Inhalt der QuelleSHAH, ASHWIN, V. NAGPAL und C. CHAMIS. „Probabilistic analysis of bladed turbine disks and the effect of mistuning“. In 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.
Der volle Inhalt der QuellePhan, Hien, und Li He. „Phasing Structural and Aerodynamic Mistuning For Leveraging Aeroelastic Performance“. In ASME Turbo Expo 2022: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/gt2022-82168.
Der volle Inhalt der QuellePhan, H. M., und L. He. „ANALYSIS OF STRUCTURALLY AND AERODYNAMICALLY MISTUNED OSCILLATING BLADEROW USING FULLY-COUPLED METHOD“. In GPPS Xi'an21. GPPS, 2022. http://dx.doi.org/10.33737/gpps21-tc-330.
Der volle Inhalt der QuelleStapelfeldt, Sina, und Christoph Brandstetter. „Suppression of Non-Synchronous-Vibration Through Intentional Aerodynamic and Structural Mistuning“. In ASME Turbo Expo 2021: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2021. http://dx.doi.org/10.1115/gt2021-59659.
Der volle Inhalt der QuelleMadden, Andrew, Matthew Castanier und Bogdan Epureanu. „Mistuning Identification of Blisks at Higher Frequencies“. In 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.
Der volle Inhalt der QuelleWHALEY, P., und J. MACBAIN. „Effects of mistuning on the forced vibration of bladed disks in subsonic flow“. In 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.
Der volle Inhalt der QuelleLian, Bo, Xiaocheng Zhu und Zhaohui Du. „Mistuning Effects on Aero-Elastic Stability of Civil Transonic Fan Blades“. In ASME Turbo Expo 2022: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/gt2022-80613.
Der volle Inhalt der QuelleGillaugh, Daniel, Alexander Kaszynski, Jeffrey M. Brown, David A. Johnston und Joseph C. Slater. „Accurate Strain Gage Limits Through Geometry Mistuning Modeling“. In 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.
Der volle Inhalt der QuelleSladojevic´, I., E. P. Petrov, M. Imregun und A. I. Sayma. „Forced Response Variation of Aerodynamically and Structurally Mistuned Turbo-Machinery Rotors“. In ASME Turbo Expo 2006: Power for Land, Sea, and Air. ASMEDC, 2006. http://dx.doi.org/10.1115/gt2006-90948.
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