Numerical Simulation Of Dilution Zone Of Aeroengine Combustor Flame Tube

The aspects of the investigation of aeroengine combustor dilution zone at home and abroad is very deeply examined in this paper, the main methods, its status and developmental trend are presented here. The basic problems of dilution zone, the theoretical base and numerical calculation method of 3D two-phase turbulence combustion are described in detail. This paper utilizes commercial software FLUENT6.2 to numerically simulate and calculate velocity field, temperature field in dilution zone and droplet track under the 3D two phase turbulent combustion for the ground idling, the altitude-small lever flying, the middling, the peak heat load and the peak conditions. By analyzing the calculation results and comparing with tests, the characters of dilution zone is well investigated. The analysis indicates that the cold-thermal zones of dilution zone determines the cold-heat zones of the temperature field at the combustor outlet; The primary function of dilution zone are deduce and equimlibium tempreture, at the same time, it can improve the uniformity of the temperature field at the combustor outlet exceed 20% and depress high tempreture zone obviously, generally the reducing quantity of tempreture exceeds 400K at major operational conditions; the burning efficiency of dilution zone influences on the burning efficiencies of the combustor, for major operational conditions the increase in burning efficiencies can exceed 6%.The velocity fields at high load level conditions are very similar; with increasing of the load, the droplet tracks show a reduction tendency. The mentioned results fit the testing results and combustor operating performances well, and it demonstrate the reasonableness and feasibility of this numerical simulation.