Details
| Original language | English |
|---|---|
| Title of host publication | Proceedings of 12th European Conference on Turbomachinery Fluid dynamics & Thermodynamics |
| Publication status | Published - 2017 |
| Event | 12th European Conference on Turbomachinery Fluid Dynamics and Thermodynamics, ETC 2017 - Stockholm, Sweden Duration: 3 Apr 2017 → 7 Apr 2017 |
Publication series
| Name | European Conference on Turbomachinery Fluid Dynamics and Thermodynamics, ETC |
|---|---|
| ISSN (Print) | 2313-0067 |
Abstract
A substructure-based reduced order model for the numerical prediction of the mistuned dynamics of bladed disks is presented. The structural mistuning is introduced to the tuned disk by blade-to-blade variations of the natural frequencies. Aeroelastic influence coefficients provide aerodynamic inter-blade and inter-modal coupling via the fluid flow. The accuracy and efficiency of the reduced modeling approach are highlighted by a comparison with conventional FEA simulations and unsteady CFD results. In total, the model reduction provides a computational saving of up to 90% while predicting the amplitudes of forced vibrations within a tolerance of 0.7%. The proposed modeling technique is used to analyze the forced response and the aeroelastic stability of an axial compressor blisk. This exemplary study reveals an attenuation of the mistuned response due to an increase in aerodynamic damping. The intentionally provoked interaction of two mode families illustrates the significance of the inter-modal aerodynamic coupling.
Keywords
- Aeroelasticity, Compressor blisk, Flutter stability, Forced response
ASJC Scopus subject areas
- Engineering(all)
- Mechanics of Materials
- Engineering(all)
- Mechanical Engineering
- Physics and Astronomy(all)
- Condensed Matter Physics
Cite this
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Proceedings of 12th European Conference on Turbomachinery Fluid dynamics & Thermodynamics. 2017. ETC2017-242 (European Conference on Turbomachinery Fluid Dynamics and Thermodynamics, ETC).
Research output: Chapter in book/report/conference proceeding › Conference contribution › Research › peer review
}
TY - GEN
T1 - Reduced order modeling of mistuned bladed disks considering aerodynamic coupling and mode family interaction
AU - Willeke, S.
AU - Keller, C.
AU - Panning-von Scheidt, L.
AU - Seume, J.
AU - Wallaschek, J.
PY - 2017
Y1 - 2017
N2 - A substructure-based reduced order model for the numerical prediction of the mistuned dynamics of bladed disks is presented. The structural mistuning is introduced to the tuned disk by blade-to-blade variations of the natural frequencies. Aeroelastic influence coefficients provide aerodynamic inter-blade and inter-modal coupling via the fluid flow. The accuracy and efficiency of the reduced modeling approach are highlighted by a comparison with conventional FEA simulations and unsteady CFD results. In total, the model reduction provides a computational saving of up to 90% while predicting the amplitudes of forced vibrations within a tolerance of 0.7%. The proposed modeling technique is used to analyze the forced response and the aeroelastic stability of an axial compressor blisk. This exemplary study reveals an attenuation of the mistuned response due to an increase in aerodynamic damping. The intentionally provoked interaction of two mode families illustrates the significance of the inter-modal aerodynamic coupling.
AB - A substructure-based reduced order model for the numerical prediction of the mistuned dynamics of bladed disks is presented. The structural mistuning is introduced to the tuned disk by blade-to-blade variations of the natural frequencies. Aeroelastic influence coefficients provide aerodynamic inter-blade and inter-modal coupling via the fluid flow. The accuracy and efficiency of the reduced modeling approach are highlighted by a comparison with conventional FEA simulations and unsteady CFD results. In total, the model reduction provides a computational saving of up to 90% while predicting the amplitudes of forced vibrations within a tolerance of 0.7%. The proposed modeling technique is used to analyze the forced response and the aeroelastic stability of an axial compressor blisk. This exemplary study reveals an attenuation of the mistuned response due to an increase in aerodynamic damping. The intentionally provoked interaction of two mode families illustrates the significance of the inter-modal aerodynamic coupling.
KW - Aeroelasticity
KW - Compressor blisk
KW - Flutter stability
KW - Forced response
UR - http://www.scopus.com/inward/record.url?scp=85043434995&partnerID=8YFLogxK
U2 - 10.29008/ETC2017-242
DO - 10.29008/ETC2017-242
M3 - Conference contribution
T3 - European Conference on Turbomachinery Fluid Dynamics and Thermodynamics, ETC
BT - Proceedings of 12th European Conference on Turbomachinery Fluid dynamics & Thermodynamics
T2 - 12th European Conference on Turbomachinery Fluid Dynamics and Thermodynamics, ETC 2017
Y2 - 3 April 2017 through 7 April 2017
ER -