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.
Flow Field Simulations of a Gas Turbine Combustor
Contributed by the International Gas Turbine Institute and presented at the International Gas Turbine and Aeroengine Congress and Exhibition, New Orleans, Louisiana, June 4–7, 2001. Manuscript received by the IGTI, November 2000; revised manuscript received March 2001. Paper No. 2001-GT-170. Review Chair: R. A. Natole.
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Barringer , M. D., Richard , O. T., Walter , J. P., Stitzel , S. M., and Thole, K. A. (July 10, 2002). "Flow Field Simulations of a Gas Turbine Combustor ." ASME. J. Turbomach. July 2002; 124(3): 508–516. https://doi.org/10.1115/1.1475742
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