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Simplified Determination of Aerodynamic Damping for Bladed Rotors: Part 1 — Experimental Validation at Rest

[+] Author Affiliations
Bernd Beirow, Thomas Maywald, Felix Figaschewsky, Christoph Rocky Heinrich, Arnold Kühhorn

Brandenburg University of Technology, Cottbus, Germany

Thomas Giersch

Rolls-Royce Deutschland Ltd & Co KG, Blankenfelde-Mahlow, Germany

Paper No. GT2016-56535, pp. V07BT34A007; 10 pages
  • ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition
  • Volume 7B: Structures and Dynamics
  • Seoul, South Korea, June 13–17, 2016
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4984-2
  • Copyright © 2016 by Rolls-Royce Deutschland Ltd & Co KG


Considering both a radial turbine rotor of a turbocharger and an axial compressor test blisk at rest, aerodynamic damping characteristics are experimentally and numerically analyzed. Linear dependencies of modal damping ratios on the ambient pressure or the acoustic impedance, respectively, could be shown within experiments carried out inside a pressure chamber. The impact of the ambient air clearly dominates the modal damping ratios compared to the minor contribution of the structure. Assuming that acoustic emission can be regarded as main source of aerodynamic damping a simplified approach for its determination is introduced which only depends on natural frequency, mode shape and acoustic impedance. It is shown that a satisfying match between experiment and computation is achieved for those cases which are dedicated to sufficiently small ratios between wave lengths of acoustic emissions and blade distances.

Copyright © 2016 by Rolls-Royce Deutschland Ltd & Co KG
Topics: Damping , Rotors



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