为研究航空发动机进气道直流喷嘴防冰冲击射流和环形流动换热特征，采用数值仿真方法开展进气道防冰腔内外流耦合换热分析，建立针对直流喷嘴防冰效果评估的无量纲特征参数(T_max ) ?、(T_min ) ?、C_(tem dev)和(T_ave ) ?，得出了同喷嘴射流角度、喷嘴位置、喷口面积比对进气道唇口表面温度和特征参数的影响，并得出了直流喷嘴防冰流动平均雷诺数Re_ave和平均努赛尔数Nu_ave的规律关系式。研究结果表明：喷嘴热气射流距离越远，防冰效果越好；喷嘴射流角度和喷嘴位置略靠近唇口内流道侧时，唇口温度均匀性越好；增大靠近进气道侧喷口的面积将提升唇口温度均匀性，但同时将增加进气道过热风险。

To investigate the heat transfer characteristics of impinging jet flow and annular recirculation in a swirl nozzle anti-icing system for engine inlet, a numerical simulation method is conducted to analyze the coupled internal-external flow and heat transfer within the anti-icing cavity. Characteristic parameters, namely Nozzle Spray Angle, Nozzle position and Nozzle area ratio, are established for evaluating anti-icing performance. The influence of these parameters on temperature distribution and thermal uniformity at the inlet lip are systematically investigated. A quantitative correlation is derived between the average Re and the average Nu for the anti-icing flow. Results show that: Increasing the standoff distance between the nozzle and the inlet lip enhances anti-icing effectiveness. Changing Nozzle Spray Angle and Nozzle Position slightly offset toward the inner side of the inlet significantly improve temperature uniformity. Increasing the area of the orifice adjacent to the inlet improves temperature uniformity but simultaneously raises the risk of overheating. These findings provide a mechanistic basis for optimization of swirl nozzle anti-icing systems.