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Experimental and Numerical Study of Stall Flutter in a Transonic Low-Aspect Ratio Fan Blisk

[+] Author Affiliations
A. J. Sanders, K. K. Hassan

Honeywell Engines, Systems and Services, Phoenix, AZ

D. C. Rabe

Air Force Research Laboratory, Wright-Patterson AFB, OH

Paper No. GT2003-38353, pp. 339-348; 10 pages
doi:10.1115/GT2003-38353
From:
  • ASME Turbo Expo 2003, collocated with the 2003 International Joint Power Generation Conference
  • Volume 4: Turbo Expo 2003
  • Atlanta, Georgia, USA, June 16–19, 2003
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-3687-8 | eISBN: 0-7918-3671-1
  • Copyright © 2003 by ASME

abstract

Experiments are performed on a modern design transonic shroudless low-aspect ratio fan blisk that experienced both subsonic/transonic and supersonic stall-side flutter. High-response flush mounted miniature pressure transducers are utilized to measure the unsteady aerodynamic loading distribution in the tip region of the fan for both flutter regimes, with strain gages utilized to measure the vibratory response at incipient and deep flutter operating conditions. Numerical simulations are performed and compared with the benchmark data using an unsteady three-dimensional nonlinear viscous computational fluid dynamic (CFD) analysis, with the effects of tip clearance, vibration amplitude, and the number of time steps-per-cycle investigated. The benchmark data are used to guide the validation of the code and establish best practices that ensure accurate flutter predictions.

Copyright © 2003 by ASME

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