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Impact of an Upstream Film-Cooling Row on Mitigation of Secondary Combustion in a High Fuel-Air Environment

[+] Author Affiliations
Brian T. Bohan, David L. Blunck

Air Force Research Laboratory, Wright-Patterson AFB, OH

Marc D. Polanka

Air Force Institute of Technology, Wright-Patterson AFB, OH

Stanislav Kostka, Naibo Jiang, Sukesh Roy

Spectral Energies, LLC, Dayton, OH

Scott D. Stouffer

University of Dayton Research Institute, Dayton, OH

Paper No. GT2012-68310, pp. 915-926; 12 pages
  • ASME Turbo Expo 2012: Turbine Technical Conference and Exposition
  • Volume 4: Heat Transfer, Parts A and B
  • Copenhagen, Denmark, June 11–15, 2012
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4470-0
  • Copyright © 2012 by ASME


In advanced gas turbine engines that feature very short combustor sections, an issue of fuel-rich gases interacting with downstream components exists. In all of these engines there are regions downstream of the primary combustion section that will require the use of film-cooling in the presence of incompletely reacted exhaust. This will lead to the possibility of additional combustion reactions resulting from the combination of unburnt fuel and oxygen-rich cooling films. Research has been accomplished to understand this secondary reaction process. This experimental film-cooling study expands the previous investigations by attempting to reduce or remove the negative effects that result from secondary combustion in the coolant film. An upstream row of holes was added to a row of previously tested shaped coolant holes to understand if the reactions could be mitigated at the downstream locations. Several combinations of cooling schemes were investigated and the heat flux downstream was measured. Planar Laser Induced Fluorescence (PLIF) was used to measure OH concentration in the combustion zones to understand where the reactions occurred. It was discovered that creating a full sheet of air upstream could effectively protect the downstream row from the negative impacts of the fuel-rich crossflow.

Copyright © 2012 by ASME



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