The LM-6000 Combustor Geometry is used as operational hardware by GE Aircraft Engines for gas turbine applications and used to test computational modeling capabilities in lean premixed and partially premixed combustion regimes. Operating in these regimes can reduce nitrogen oxide emmissions, but also can be suseptible to combustion and pressure instabilities. One way to better understand this phenomenon, is through Fluent's Large Eddy Simulation (LES) capability, combined with a partially premixed combustion model, which solves the mean and variance of mixture fraction and reaction progress variable. Three different sub-grid flame speed models were investigated for this analysis. A direct comparison of the predicted mean properties and experiment indicate good agreement.

Temperature contours on a flame surface and contours of vorticity magnitude on the mid-plane of a gas turbine combustor.
Courtesy of General Electric.

Courtesy of GE Aircraft Engines