Numerical and experimental study of the combustion performance of an integrated inclined combustor

To shorten the length of an aero-engine combustor and reduce its weight, we propose an integrated inclined combustor. A combination of numerical calculations and experimental research methods is employed to conduct relevant research on the cold and combustion flow fields and ignition dynamic processes of the integrated inclined combustor. Results show that the inclination angle of the swirler has minimal effect on the total pressure loss and combustion efficiency of the integrated inclined combustor. However, as the swirler's inclination angle increases, the uniformity of the outlet temperature distribution and recirculation flow rate of the primary combustion zone decrease. Furthermore, when the integrated inclined combustor is ignited, the flame does not propagate symmetrically to both sides in the circumferential direction but propagates faster along the inclination direction of the swirler.