Abstract
Many modern industrial gas-turbine spray combustors are characterized with multiple swirlers and distributed fuel injection for rapid mixing and stabilization. This chapter reviews an experimental and computational study of the cold flow field of a nonreacting combustor in which the air is introduced through a Triple Annular Swirler (TAS). Multiple combinations of swirlers with different swirl levels and directions are tested with the air discharged into the atmosphere or into a confining chamber. The experiments demonstrate that a central recirculation zone and an annular jet with internal and external shear layers essentially characterize the flowfield downstream of TAS. The Central Toroidal Recirculation Zone (CTRZ) region is axisymmetric but the jet contains imprints of the internal flow and has some nonaxisymmetric features. Comparison of experimental results with LES and RANS simulations confirms the observations and exhibit that the asymmetry related to the effect of the internal swirling vanes on the jet flow. Compared to unconfined case, flow with a chamber shows an enlarged CTRZ region and a recirculation region in the expansion corner and reduced concentration of turbulence intensity in the jet region.
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