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Reduction of Forced Response Levels for Bladed Discs by Mistuning: Overview of the Phenomenon

[+] Author Affiliations
E. P. Petrov

Imperial College London, London, UK

Paper No. GT2010-23299, pp. 1039-1051; 13 pages
doi:10.1115/GT2010-23299
From:
  • ASME Turbo Expo 2010: Power for Land, Sea, and Air
  • Volume 6: Structures and Dynamics, Parts A and B
  • Glasgow, UK, June 14–18, 2010
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4401-4 | eISBN: 978-0-7918-3872-3
  • Copyright © 2010 by Rolls-Royce plc

abstract

The newly-revealed phenomenon of reduction of forced response levels in a mistuned bladed disc to levels significantly (e.g. by a factor of two and more) lower than that of its tuned counterpart is studied in detail on an example of a realistic bladed disc. Statistical properties of the amplification factor of the mistuned forced response calculated with aero-effects included have been studied for cases of random blade mistuning and for mistuned blade rearrangements. Optimization search for the best mistuning patterns providing maximum forced response reduction effect have been performed, and the robustness of the optimum mistuning patterns has been demonstrated. The combined effect of the aerodynamic and structural damping on the response reduction is assessed. It is shown that the new phenomenon is of major practical significance and has to be taken into account in analysis of the forced response and design decisions.

Copyright © 2010 by Rolls-Royce plc
Topics: Disks

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