Influence of inlet swirl on pattern factor and pressure loss in an aero engine combustor

The effect of compressor exit swirl angle (theta sw) at the intake of an aero engine combustor on the exit temperature non-uniformity (pattern factor) and combustor total pressure loss is investigated. Experiments are conducted in the engine test rig, measuring the gas temperature and pressure at the inlet and exit planes of the combustor. These parameters are measured at distinct locations along the circumferential and radial directions in the engine test facility. Simulations are carried out using RANS based turbulence modeling and reacting flow approach with Ansys CFX commercial code. The predicted results are validated with experimental data at 5 degrees swirl angle. The swirl angle at the combustor intake is further varied from 0 degrees to 15 degrees and 4 cases (0 degrees, 5 degrees, 10 degrees and 15 degrees) has been considered to predict the effect on the combustor pattern factor and pressure loss. The changes in the flow structure inside the combustion chamber for all these 4 cases are reported in detail. The pattern factor varies from 0.34 to 0.49 as swirl angle changes from 0 degrees to 15 degrees. The lowest pattern factor of 0.34 occurs at 10 degrees swirl angle. However a linear increase in combustor total pressure loss from 5.85% to 6.53% is predicted with the change in swirl angle from 0 degrees to 15 degrees(.)