加力隔热屏及中心锥冷却对二元收扩排气系统红外抑制效果数值分析

Aiming at the turbofan engine with a two-dimensional convergent-divergent（2D C-D）nozzle exhaust system，the effects of the afterburner heat shield and cone film cooling on the temperature of components were investigated numerically，and the infrared suppression of the cooling measures on the exhaust system and the consequent changes in thrust coefficient was revealed. The results show that the surface temperature of the heat shield can be effectively reduced by film cooling of the afterburner heat shield，and the maximum peak reduction is 10.3%，and the structure of the afterburner heat shield and the different inclination of the film holes affect the core and bypass flow distribution.Film cooling of the afterburner heat shield mainly suppresses infrared radiation（IR）from 30°~75°，and the radiation intensity can be reduced by 8%~25%，but at the same time，the thrust coefficient is reduced by up to 5.3×10^-3.After film cooling is taken for the afterburner heat shield and the cone，the surface temperature of the cone is obviously reduced，and the infrared suppression from 0°~10° is significant，its radiation intensity decreases by up to 31.3%，the consequent loss of thrust coefficient does not exceed 3.0×10^-3