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FLOW DYNAMICS IN A SWIRLING JET COMBUSTOR

Fernando F. Grinstein
Laboratory for Computational Physics and Fluid Dynamics Naval Research Laboratory, Washington DC, 20375-5344, USA

Timothy R. Young
Naval Research Laboratory, Washington DC 20375-5344, USA

G. Li
Engineering Research Center, University of Cincinnati, Cincinnati, OH 45221, USA

E.J. Gutmark
Engineering Research Center, University of Cincinnati, Cincinnati, OH 45221, USA

G. Hsiao
General Electric Aircraft Engine Company, Cincinnati, OH 45215, USA

H.C. Mongia
General Electric Aircraft Engine Company, Cincinnati, OH 45215, USA

Abstract

A hybrid simulation approach is used to investigate the flow patterns in an axisymmetric swirl combustor configuration. Effective inlet boundary conditions are based on velocity data from RANS or actual laboratory measurements at the outlet of a fuel-injector nozzle, and LES is used to study the unsteady non-reactive flow dynamics within the combustor. Case studies ranging from single-swirler to more complex multi-swirler nozzles are presented to emphasize the importance of initial inlet conditions on the behavior of the swirling flow entering a sudden expansion area, including swirl and radial numbers, inlet length, and characteristic velocity profiles.