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Effects of Flow Control on Forced Response and Performance of a Transonic Compressor

[+] Author Affiliations
S. Todd Bailie, Wing F. Ng, Alfred L. Wicks

Virginia Polytechnic Institute and State University, Blacksburg, VA

William W. Copenhaver

U.S. Air Force Research Laboratory, Wright-Patterson AFB, OH

Paper No. GT2002-30008, pp. 67-74; 8 pages
doi:10.1115/GT2002-30008
From:
  • ASME Turbo Expo 2002: Power for Land, Sea, and Air
  • Volume 1: Turbo Expo 2002
  • Amsterdam, The Netherlands, June 3–6, 2002
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-3606-1 | eISBN: 0-7918-3601-0
  • Copyright © 2002 by ASME

abstract

The main contributor to the high-cycle fatigue of compressor blades is the response to aerodynamic forcing functions generated by an upstream row of stators or inlet guide vanes. Resonant response to engine order excitation at certain rotor speeds is especially damaging. Studies have shown that flow control by trailing edge blowing (TEB) can reduce stator wake strength and the amplitude of the downstream rotor blade vibrations generated by the unsteady stator-rotor interaction. In the present study, the effectiveness of TEB to reduce forced blade vibrations was evaluated in a modern transonic compressor rig. A row of wake generator (WG) vanes with TEB capability was installed upstream of the rotor, which was instrumented with strain gages. Data was collected with and without TEB at various rotor speeds involving resonance crossings. Using 0.8% of the compressor core flow for TEB along the full WG-span, rotor blade strain was reduced by 66% at the first torsional resonance crossing. Substantial reductions were also achieved with only partial span TEB. The results demonstrate the effectiveness of the TEB technique for reducing rotor vibrations in the complex flow environment of a closely-spaced transonic stage row. Moderate increases in stage performance were also measured.

Copyright © 2002 by ASME

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