The problem of determining the worst mistuning patterns is formulated and solved as an optimization problem. Maximum resonant amplitudes searched across the many nodes of a large-scale finite element model of a mistuned bladed disk and across all the excitation frequencies in a given range are combined into an objective function. Individual blade mistuning is controlled by varying design parameters, whose variation range is constrained by manufacture tolerances. Detailed realistic finite element models, which have so far only been used for analyzing tuned bladed disks, are used for calculation of the forced resonant response of mistuned assemblies and for determination of its sensitivity coefficients with respect to mistuning variation. Results of the optimum search of mistuning patterns for some practical bladed disks are analyzed and reveal higher worst cases than those found in previous studies.
Analysis of the Worst Mistuning Patterns in Bladed Disk Assemblies
Contributed by the International Gas Turbine Institute (IGTI) of THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS for publication in the ASME JOURNAL OF TURBOMACHINERY. Paper presented at the International Gas Turbine and Aeroengine Congress and Exhibition, New Orleans, LA, June 4–7, 2001; Paper 2001-GT-0292. Manuscript received by IGTI, December 2000, final revision, March 2001. Associate Editor: R. Natole.
- Views Icon Views
- Share Icon Share
- Cite Icon Cite
- Search Site
Petrov , E. P., and Ewins, D. J. (December 1, 2003). "Analysis of the Worst Mistuning Patterns in Bladed Disk Assemblies ." ASME. J. Turbomach. October 2003; 125(4): 623–631. https://doi.org/10.1115/1.1622710
Download citation file:
- Ris (Zotero)
- Reference Manager