@inproceedings{3cdabd3fe55447f2b44893132d134d09,
title = "Flow field simulations of a gas turbine combustor",
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 question.",
author = "Barringer, {Michael David} and Richard, {O. T.} and Walter, {J. P.} and Stitzel, {S. M.} and Thole, {Karen Ann}",
year = "2001",
doi = "10.1115/2001-GT-0170",
language = "English (US)",
isbn = "9780791878521",
series = "Proceedings of the ASME Turbo Expo",
publisher = "American Society of Mechanical Engineers (ASME)",
booktitle = "Heat Transfer; Electric Power; Industrial and Cogeneration",
note = "ASME Turbo Expo 2001: Power for Land, Sea, and Air, GT 2001 ; Conference date: 04-06-2001 Through 07-06-2001",
}