Boundary condition effects on nonreacting and reacting flows in a multiswirl combustor

Detailed measurements of velocity statistics, temperature distribution, flame chemiluminescence, and emission characteristics in a lean direct fuel injection multiswirl gas turbine combustor are presented. The inlet and exit boundary conditions, including the mixing, tube length and the exhaust nozzle contraction ratio, were modified to emphasize the effects of these boundary conditions on the characteristics of nonreacting and reacting flows. Velocity statistics, including mean and turbulence kinetics, were measured by using stereoscopic particle image velocimetry in a cylindrical combustor chamber for isothermal anti reacting flow cases. The velocity spectra at different locations were measured using hot-wire anemometry. The temperature distribution along the combustor radial direction was measured using type-B fine thermocouple at different axial locations for a variety of multi-swirl configurations. The exhaust emissions of NOx and CO were measured as a function of fuel/air ratio. The data along with the detailed description of the experimental setup and operating conditions can be used to validate modeling approaches to swirling flows, the turbulence/chemistry interaction, and large-eddy simulation for multiswirl gas turbine combustors.