Heavy duty gas turbine front stages compressor blades aero-elastic behavior is deeply analyzed and investigated by means of an uncoupled, non-linear and time-accurate CFD URANS solver. The travelling-wave approach and the energy method have been applied in order to assess the aerodynamic damping (in terms of logarithmic decrement) for each inter blade phase angle (IBPA) and thus to localize the flutter stability region. The work is mainly focused on a sensitivity analysis with respect to blade operating conditions, eigen-mode shapes and frequency in order to improve the understanding of flutter mechanism and to identify the key parameters. Transonic, supercritical and subsonic blades are investigated at different operating conditions with their corresponding eigenmode and eigen-frequency (first and second flexural mode and first torsional). The results show that non-linear effects can be neglected for subsonic blades. Besides, the modal-shape and the shock structure, if any, are identified to play a key role for flutter stability.
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ASME Turbo Expo 2015: Turbine Technical Conference and Exposition
June 15–19, 2015
Montreal, Quebec, Canada
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
978-0-7918-5677-2
PROCEEDINGS PAPER
Sensitivity Analysis to Flutter for Front Stages Compressor Blades Available to Purchase
Marcello Benvenuto,
Marcello Benvenuto
Ansaldo Sviluppo Energia, Genova, Italy
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Andrea Silingardi,
Andrea Silingardi
Ansaldo Sviluppo Energia, Genova, Italy
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Pio Astrua,
Pio Astrua
Ansaldo Sviluppo Energia, Genova, Italy
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Stefano Cecchi
Stefano Cecchi
Ansaldo Sviluppo Energia, Genova, Italy
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Marcello Benvenuto
Ansaldo Sviluppo Energia, Genova, Italy
Andrea Silingardi
Ansaldo Sviluppo Energia, Genova, Italy
Pio Astrua
Ansaldo Sviluppo Energia, Genova, Italy
Stefano Cecchi
Ansaldo Sviluppo Energia, Genova, Italy
Paper No:
GT2015-42588, V07BT34A003; 9 pages
Published Online:
August 12, 2015
Citation
Benvenuto, M, Silingardi, A, Astrua, P, & Cecchi, S. "Sensitivity Analysis to Flutter for Front Stages Compressor Blades." Proceedings of the ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. Volume 7B: Structures and Dynamics. Montreal, Quebec, Canada. June 15–19, 2015. V07BT34A003. ASME. https://doi.org/10.1115/GT2015-42588
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