Numerical Analysis of Turbulent Combustion in a Model Swirl Gas Turbine Combustor

Figure 6

Predicted fields of axial velocity at an arbitrary time step in a plane through combustor by the mixture fraction-reaction progress variable based LFM for NG-FGR20 flame: (a) URANS-SST, (b) URANS-RSM, and (c) LES.

(a)

(b)

(c)