Flow field simulations of a gas turbine combustor

Michael David Barringer, O. T. Richard, J. P. Walter, S. M. Stitzel, Karen Ann Thole

Research output: Chapter in Book/Report/Conference proceedingConference contribution

8 Scopus citations


The flow field exiting the combustor in a gas turbine engine is quite complex considering the presence of large dilution jets and complicated cooling schemes for the combustor liner. For the most part, however, there has been a disconnect between the combustor and turbine when simulating the flow field that enters the nozzle guide vanes. To determine the effects of a representative combustor flow field on the nozzle guide vane, a large-scale wind tunnel section has been developed to simulate the flow conditions of a prototypical combustor. This paper presents experimental results of a combustor simulation with no downstream turbine section as a baseline for comparison to the case with a turbine vane. Results indicate that the dilution jets generate turbulence levels of 15-18% at the exit of the combustor with a length scale that closely matches that of the dilution hole diameter. The total pressure exiting the combustor in the near wall region neither resembles a turbulent boundary layer nor is it completely uniform putting both of these commonly made assumptions into question.

Original languageEnglish (US)
Title of host publicationHeat Transfer; Electric Power; Industrial and Cogeneration
PublisherAmerican Society of Mechanical Engineers (ASME)
ISBN (Print)9780791878521
StatePublished - 2001
EventASME Turbo Expo 2001: Power for Land, Sea, and Air, GT 2001 - New Orleans, LA, United States
Duration: Jun 4 2001Jun 7 2001

Publication series

NameProceedings of the ASME Turbo Expo


OtherASME Turbo Expo 2001: Power for Land, Sea, and Air, GT 2001
Country/TerritoryUnited States
CityNew Orleans, LA

All Science Journal Classification (ASJC) codes

  • General Engineering


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