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Robust Analysis of Design in Vibration of Turbomachines

[+] Author Affiliations
Moustapha Mbaye, Christian Soize, Evangeline Capiez-Lernout

Université Paris-Est, Marne-la-Vallée, France

Jean-Philippe Ousty

Turbomeca, Bordes, France

Paper No. GT2009-59651, pp. 387-396; 10 pages
doi:10.1115/GT2009-59651
From:
  • ASME Turbo Expo 2009: Power for Land, Sea, and Air
  • Volume 6: Structures and Dynamics, Parts A and B
  • Orlando, Florida, USA, June 8–12, 2009
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4887-6 | eISBN: 978-0-7918-3849-5
  • Copyright © 2009 by ASME

abstract

In the context of turbomachinery design, a small variation in the blade characteristics due to manufacturing tolerances can affect the structural symmetry creating mistuning which increases the forced response. However, it is possible to detune the mistuned system in order to reduce the forced response amplification. The main technologic solutions to introduce detuning are based on modifying blade material properties, the interface between blade and disk, or the blade shape. This paper presents a sensitivity analysis of mistuning for a given detuning in unsteady aeroelasticity. Detuning is performed by modifying blade shapes. The different kinds of blades obtained by those modifications are then distributed on the disk circumference. A new reduced-order model of the detuned disk is constructed using the cyclic modes of the different sectors which can be obtained from a usual cyclic symmetry modal analysis. Finally a stochastic analysis using a non-parametric probabilistic method to take model and system parameters uncertainties into account in the computational model is performed.

Copyright © 2009 by ASME

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