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.
- International Gas Turbine Institute
Flow Field Simulations of a Gas Turbine Combustor
- Views Icon Views
- Share Icon Share
- Search Site
Barringer, MD, Richard, OT, Walter, JP, Stitzel, SM, & Thole, KA. "Flow Field Simulations of a Gas Turbine Combustor." Proceedings of the ASME Turbo Expo 2001: Power for Land, Sea, and Air. Volume 3: Heat Transfer; Electric Power; Industrial and Cogeneration. New Orleans, Louisiana, USA. June 4–7, 2001. V003T01A048. ASME. https://doi.org/10.1115/2001-GT-0170
Download citation file: