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Single-Shot Spontaneous Raman Scattering Measurements In A Reverse-Flow Aeroengine Model Combustor Under Elevated Inlet Temperature And Pressure

Monitoring scalar fields within aero-engine combustor is of particular importance for performance promotion and engine failure diagnostics. Due to harsh operating conditions and quite limited space, direct measurements of combustion state within near-real conditioned engine combustor were rarely reported. Therefore, this paper reports spontaneous Raman scattering (SRS) measurements of temperature and major species, such as CO2, H2O, CO, N2, within a reverseflow model combustor fueled by kerosene under elevated incoming temperature of 500 K and pressure of 5 bar. The model combustor was on purposely designed to reserve both outer shell and inner liner, and the liquid kerosene was fueled with a customized atomizer. The SRS measurement were conducted at 10 characteristic spatial locations and varying equivalence ratio. The measured species and temperature revealed strong effects of turbulence-chemistry interaction and deviation from chemical equilibrium. Together with the CFD simulation, the SRS data was used to evaluate the performance of the model combustor.