T.: Mesh dependency of turbulent reacting Large-Eddy Simulations in a gas turbine combustion chamber

Summary. Convergence of reacting LES predictions for an aeronautical gas turbine combustion chamber is analysed in terms of mesh resolution. To do so three fully unstructured meshes containing respectively 1.2, 10.6 and 43.9 million tetrahedra are used to compute this fully turbulent reacting flow. Resolution criteria obtained from the mean velocity and reacting fields depict different convergence behaviors. Reacting fields and more specifically combustion regimes are seen to be slightly grid dependent while maintaining mean global combustion quantities