Abstract
The effect of swirler/prefilmer modules on spatially and temporally resolved gas temperature were experimentally investigated for better understanding of flame stability and flow structure. Temperature measurements were carried out by using coherent anti-Stokes Raman spectroscopy(CARS) at several positions within the aero-engine combustor sector rig burning standard kerosene fuel. Research rig representing a 36° sector from a full annular combustor was installed and run at simulated ground idle conditions, showing features of flow mixing within the burning rig. Inlet air was heated and compressed up to 530K and 3.2bar. Air flow rate and overall A/F ratio were 1.1kg/s and 90 respectively. Experiments were carried out at three conditions to see the individual effect of swirl direction and prefilmer. Temperature PDFs were obtained from 500-single shot spectra to investigate the temperature fluctuations in the combustor. Results revealed that a strong reverse flow zone is formed by the lean fuel module with radial swirler. And it also shows that swirl direction of fuel module significantly affects to the shape of recirculation zone, while the presence of prefilmer forms more uniform spray characteristics and pushes the recirculation zone in further downstream.
