Flow field simulations of a gas turbine combustor

M. D. Barringer, O. T. Richard, J. P. Walter, S. M. Stitzel, K. A. Thole

Research output: Contribution to journalArticlepeer-review

52 Scopus citations

Abstract

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 questions.

Original languageEnglish (US)
Pages (from-to)508-516
Number of pages9
JournalJournal of Turbomachinery
Volume124
Issue number3
DOIs
StatePublished - Jul 2002

All Science Journal Classification (ASJC) codes

  • Mechanical Engineering

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