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Reduced-Order Modeling and Experiment for Turbomachinery Stall Flutter

[+] Author Affiliations
George Scott Copeland

United Technologies Research Center, East Hartford, CT

Gonzalo J. Rey

Pratt and Whitney Aircraft Engines

Paper No. IMECE2002-33056, pp. 139-145; 7 pages
doi:10.1115/IMECE2002-33056
From:
  • ASME 2002 International Mechanical Engineering Congress and Exposition
  • 5th International Symposium on Fluid Structure Interaction, Aeroelasticity, and Flow Induced Vibration and Noise
  • New Orleans, Louisiana, USA, November 17–22, 2002
  • Conference Sponsors: Applied Mechanics Division
  • ISBN: 0-7918-3659-2 | eISBN: 0-7918-1691-5, 0-7918-1692-3, 0-7918-1693-1
  • Copyright © 2002 by ASME

abstract

A reduced-order model for stall flutter of turbomachinery is presented. The model is based on simplified physics (actuator disk modeling of bladerows, typical section aeroelastic model) and the measured steady performance characteristic. The model is not intended to be predictive, though it has been shown to be “tunable” to stability measurements of the test rig. The objective of the effort is to estimate the relative sensitivity of flutter damping to system parameters. It is found that predictions are in good agreement with measured test rig data and industry experience.

Copyright © 2002 by ASME

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