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A Study of Spontaneous Transition in Swirl-Stabilized Flames

[+] Author Affiliations
Isaac Boxx, Klaus Peter Geigle, Wolfgang Meier

German Aerospace Center (DLR), Stuttgart, Germany

Campbell D. Carter

Air Force Research Laboratory, Wright-Patterson AFB, OH

Benjamin Akih-Kumgeh, Jacques Lewalle

Syracuse University, Syracuse, NY

Paper No. GT2017-64438, pp. V04BT04A016; 12 pages
doi:10.1115/GT2017-64438
From:
  • ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition
  • Volume 4B: Combustion, Fuels and Emissions
  • Charlotte, North Carolina, USA, June 26–30, 2017
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-5085-5
  • Copyright © 2017 by ASME

abstract

The goal of this study was to select and test some analysis tools to identify and characterize precursors to the onset of thermo-acoustic pulsation in a gas turbine combustor. The target flame was a turbulent, swirl-stability ethylene-air flame operated at ϕ = 0.91, and 5 bars pressure. 3-component stereo-particle image velocimetry (PIV) measurements, acquired at 9.3 kHz over periods of approximately 4 seconds were used to characterize the flow-field near the exit plane of the combustor. Acoustic measurements and OH*-chemiluminescence images were acquired synchronously, with OH* images acquired at every third cycle of the PIV measurement system.

Analysis revealed the presence of two characteristic frequencies in the data for the stable flame; a 475 Hz oscillation associated with the shear-layer dynamics and a weak thermo-acoustic oscillation 610 Hz. In the excited state, a 720 Hz self-excited thermo-acoustic oscillation dominated combustor dynamics. A possible precursor event was identified in the form of a 635 Hz oscillation that appeared in the data 0.15s prior to transition. Bandpass filtering of the velocity data at this frequency showed this oscillation originates in the outer recirculation zone of the combustor.

Copyright © 2017 by ASME
Topics: Flames

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