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Application of Reduced-Order Aerodynamic Modeling to the Analysis of Structural Uncertainty in Bladed Disks

[+] Author Affiliations
K. Willcox, J. Peraire

Massachusetts Institute of Technology, Cambridge, MA

Paper No. GT2002-30680, pp. 1257-1265; 9 pages
doi:10.1115/GT2002-30680
From:
  • ASME Turbo Expo 2002: Power for Land, Sea, and Air
  • Volume 5: Turbo Expo 2002, Parts A and B
  • Amsterdam, The Netherlands, June 3–6, 2002
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-3610-X | eISBN: 0-7918-3601-0
  • Copyright © 2002 by ASME

abstract

Blade-to-blade variations can significantly impact the operation of bladed disks. In this paper, a method is presented for assessing the effects of these variations using a high-fidelity aerodynamic analysis. Systematic model reduction is applied to a high-order computational fluid dynamics code using the proper orthogonal decomposition technique. This results in a low-order model suitable for time domain computations of mistuning effects. The model is shown to capture the dynamics of the aeroelastic system more accurately than with a traditional influence coefficient approach. Results are presented for a bladed disk with structural uncertainty, where the blade frequencies exhibit random variations about a nominal state. Finally, the concept of a robust design is explored, in which intentional variation is introduced to the system in an attempt to alleviate the ill-effects of random variations. The approach can also be extended to consider aerodynamic uncertainty, which may arise from geometric variations.

Copyright © 2002 by ASME
Topics: Modeling , Disks , Uncertainty

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