Numerical Study On Combustion Performance Of Reverse Flow Combustor With Swirl Cup

The general situation of the investigation of reverse-flow combustor at home and abroadis very deeply examined in the paper, the main methods, its status and developmental trendare presented here. The basic parameters of aeroengine combustor, the theoretical base ofnumerical calculation method are described simply. By using Fluent, the flow characteristicsof the swirl cup in the cylinder was investigated, and on this basis, the velocity field, thetemperature distribution and the pressure drop in aeroengine combustor under the3D twophase turbulent combustion for the cruise, and design conditions were numerically simulatedhere. The swirl number of the first swirl cup is2.86and it is0.66for the second, But the swirlcup formed very weak backflow itself, and for which the main hole of the liner was needed.The second swirl cup played a leading role, which showed that the swirl number is not theonly factor to the airflow’s direction. The combustor numerical simulation results showed that:1) there formed an obvious backflow zone in the dome, which was interrupted by the outermain holes. The jet flow was asymmetrical for main hole of the inner and outer liner. The jetflow of outer main hole nearly passed through the whole liner, but it was very shallow for theinner ones. The depth of the outer dilution was about two thirds of the liner height, and it wasone third for the inner, which had benefit for the outer temperature debugging. The exitairflow of the two swirl cup had intersection, which lead to rapid propagation of flame.2) thetemperature distribution was reasonable in the combustor, and the exit temperaturedistribution was suitable for the turbine. The calculated OTDF for cruise and designconditions were0.28and0.263respectively, and the RTDF were0.075and0.078, the totalpressure loss were3.08%and2.99%. The simulation results accords well with the experiment.3) the NOx emission is rare on the cruise condition, and there’s few on the design point. Theseresults have some guidance for the reverse-flow combustor design.