Flame–cooling air interaction in an effusion-cooled model gas turbine combustor at elevated pressure

摘要: The focus of this work is the investigation flame–cooling air interaction by means wall temperature (2D themographic phosphor thermometry), gas phase (coherent anti-Stokes Raman spectroscopy), flame structure (planar laser-induced fluorescence OH) and flow field (particle image velocimetry) measurements in an effusion-cooled single sector model turbine combustor. rig operated under close-to-reality boundary conditions, i.e., elevated combustor inlet increased system pressure. Parametric variations important parameters, namely swirl, staging effusion cooling mass are conducted to investigate their effect on total film effectiveness. Furthermore, we derive a dimensionless intensity parameter basis OH-PLIF data. latter revealed higher for fully premixed operation at low swirl number—a trend that reversed numbers, where partially combustion mode leads intensities. This reflected as well resulting Peak varies up $$150\,{\text {K}}$$ across all parametric $$200\,{\text axial direction liner given condition. corresponds variation effectiveness between 0.45–0.57 0.45–0.62, respectively.