LARGE-EDDY SIMULATION AND DETAILED MODELING OF SOOT EVOLUTION IN A MODEL AERO ENGINE COMBUSTOR

In order to exploit the potential of computational modeling for the reduction of particulate emissions in future aero engines, reliable modeling approaches applicable in system scale simulations are required. Achieving this goal crucially depends on bridging the gap between academic test cases often used for model validation and real world applications. In this work, Large-Eddy Simulations of a model aero engine combustor experimentally investigated at the German Aerospace Center (DLR) are performed using an integrated modeling approach based on the Radiation Flamelet/Progress Variable model and a detailed bivariate soot particle description combined with the Hybrid Method of Moments. First, a non-reacting flow case is simulated to validate the computational setup in absence of the complex interaction of turbulence, chemistry, and soot. Then, the reacting flow is analyzed in terms of velocity, temperature, and soot volume fraction predictions. Measured velocity profiles for the non-reactive case are very well predicted. For the fired combustor, the velocity and temperature fields are well predicted. Soot is overpredicted by the simulation, but qualitatively in reasonable to good agreement with the experimental data.