液冷塞式二元喷管对发动机红外辐射影响仿真及实验研究

数值仿真和实验研究了液冷塞锥不同冷却效率对配装二元寨式喷管的发动机红外辐射特征影响。研究结果表明:对塞锥进行冷却后,可有效降低发动机尾向3μm~5um波段红外辐射特征。对于发动机喷流红外辐射,采用塞锥液冷措施可有效降低喷流红外辐射,当冷却水量为0.1kg/s、0.2kg/s和0.3kg/s时,喷流0°~90°红外辐射强度均值分别可降低31.9%、53.5%和68.7%。对于发动机固体辐射,塞锥冷却效率在0.3~0.7范围,发动机尾向0°~30°固体红外辐射特征随冷却效率的升高而迅速降低;当冷却效率达到0.7以上时,发动机机尾向 0°~30°固体红外辐射特征降低趋势减缓。实验结果表明当冷却水量为 0.3kg/s 时,塞锥冷却效率达到 0.876,相对于基准发动机,隐身型发动机在0°~10°红外辐射均值可降低94.77%。

Simulation and Experimental Study on the Influence of Liquid Cooling Two-dimensional Plug Nozzle on Engine Infrared Radiation

Numerical simulation and experimental research were conducted to investigate the effect of different cooling efficiency of liquid cooled plug cones on the infrared radiation characteristics of aeroengines equipped with two-dimensional plug nozzle. The research results indicate that cooling the plug cone can effectively reduce tail direction Infrared radiation characteristics of the aeroengine in 3μm～5μm waveband. For the infrared radiation of the aeroengine jet, liquid cooled plug cones can effectively reduce the infrared radiation of the jet. When the cooling water flow is 0.1kg/s, 0.2kg/s and 0.3kg/s, the mean value of jet infrared radiation characteristics at 0 °~90 ° can be reduced by 31.9%, 53.5% and 68.7% in 3μm～5μm waveband.For the wall surface radiation of the aeroengine,when the cooling efficiency of the plug cone is in the range of 0.3~0.7, the wall surface infrared radiation characteristics of the aeroengine at the tail direction 0 °~30 ° decrease rapidly with the increase of cooling efficiency; When the cooling efficiency reaches above 0.7, the decreasing trend of wall surface infrared radiation characteristics at the tail direction 0 °~30 ° of the aeroengine slows down. The experimental results show that when the cooling water flow is 0.3kg/s, the cooling efficiency of the plug cone reaches 0.876. The mean value of the aeroengine infrared radiation at 0 °~10 ° can be reduced by 94.77%.