Gas turbine flow and combustion simulations using LES and tabulated chemistry
Modern gas turbines for power generation or aircraft propulsion are constraint by legislation to produce less unburnt hydrocarbons, CO and NOx emissions. Reduction of these emissions is commonly achieved by operating under lean (i.e. sub-stoichiometric) conditions be means of severe dilution with air. These diluted flames have a very narrow operating window where combustion takes place in a stable way. Flame stability can be achieved by introducing a strong swirling motion to the combustion air entering the combustion chamber: these swirling motions lead to strong recirculation inside the combustion chamber, which in turn stabilize the flame. The DLR gas turbine model combustor is a well-documented representative test case, for which high quality measurement data is available for both flow field and chemical species. Measurement data is available for three operating conditions, varying in both thermal load and (global) equivalence ratio. Figure 1 illustrates the model combustor geometry, the computational domain used in previous numerical simulations and a slice of the geometrical discretization of the (previously used) computational domain.
Contact: Bendiks-Jan BOERSMA
( or 015-2787979) Giel RAMAEKERS
( or 043-3030022).
More information can be found here.


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