Numerical Simulation Of The Temperature Field Under The Transition Condition In An Aero Engine Combustor

The aspects of the investigation of aeroengine combustor 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 aeroengine combustor, the theoretical base and numerical calculation method of 3D two-phase turbulence combustion are described in detail. By means of commercial software FLUENT, the velocity field, the temperature field and the droplet track in aeroengine combustor under the 3D two phase turbulent combustion for the ground idling, the peak, the cruise, and maximum-continuous conditions are numerically simulated and calculated here. By analyzing the calculation results and combining with the results of engine transition condition tests, the temperature field characters of transition condition are well investigated. The analyses indicate: the maximum increasing amounts of the mean temperature and the peak temperature arrive in the acceleration process of the transition condition from the idling to peak power, and for this combustor, the maximum increasing amounts of the mean temperature in the main combustion, dilution two zones and at outlet in the flame tube is 664K, 763K and 718K respectively, the minimum increasing amounts of the mean temperatures arrive in the acceleration process from the idling to cruising condition (power is 51%), for three zones, they are 32K, 135K, 93K respectively. The peak values for the mean temperature changing rate depend tightly on acceleration times, and arrive in the acceleration process form the idling to the maximum continuous condition, and for the relative three zones, the temperature changing rates are 324K/s, 307.6K/s, 416K/s respectively. The minimum value of the temperature changing rate arrive also in the acceleration process from the idling to the cruising condition (power is 51%), in the relative zones, the temperature changing rates are 24K/s, 67K/s and 47K/s. These results have very important meaning for researching of the transition condition performance in engine combustor.