1. Host of these problems can be answered readily using Computational Fluid Dynamics (CFD) analysis and flow visualization experiment. Therefore, a numerical simulation of the mixing performance of a generic symmetric quick-mix section is sununarized in this paper, Water flow visualization experiment using laser-induced fluorescence technique is also employed to verify the 3-D CFD simulation results at selected conditions. The analysis considers non-reacting jet-mixing to concentrate on the fluid mechanics aspect of the process. Similar to Talpallikar et al. (1992). typical high pressure, high temperature air flowproperties for combustorare UI for the jets and cross-flow. Since chemichd reaction is not considered here, temperature serves as a passive scalar for the niixing process for adiabatic wall boundary conditions.
2. A steady-state 3-D Navier-Stokes solver (Talpallikar et al., 1992) is used to investigate the radial mixer performance, by simulatingthe non-reacting flowfield in a generic tubular RQL combustor quick-mix section. The computation is based on the finite volume formulationand a variant of thepressure-based SIMPLEC (Van Doormaal and Raithby, 1984) algorithm. The governing equations are formulated using a fully implicit and strongly conservative formulation and solved with a modified form of Stone's strongly implicit solver (1968). An upwind differencing scheme is used for the convection terms. Turbulence properties are modeled using the baseline k-E model (Launder and Spalding, 1974) with wall functions in this study. Typically, the residualsdrop four to five orders of magnitude within two hundred iterations without optimal tuning of the under-relaxation coefficient Slanted slotsand swirling flowcases, howeve&
3. undaries) must be used for the computation %main. Atransfinite interpolation procedure is used to generate the grids for the slanted slot case, similar to the approach of rang etal (1992). Fig. 1 shows the typical grid systems used in the straight-slot and slanted-slot cases. Grid density converges to the jet center and to the wall to resolve the strong velocity gradients in these areas.