本研究针对大涵道比涡扇发动机唇口防冰问题，采用数值模拟方法，对比分析了定向流喷嘴旋流增强器（Director Flow Nozzle Swirl Enhancer, DFNSE）与传统笛形管两种引气防冰方式的加热性能，并系统研究了DFNSE关键几何参数（扭转角、流道数、环形流道收扩比）对防冰效果的影响。结果表明：在相同引气条件下，DFNSE相较于笛形管具有更高的外蒙皮平均温度、更低的引气压力与热积聚，对发动机性能影响更小；通过对不同结构参数下换热效果的数值模拟发现，扭转角、流道数与收扩比对加热均匀性和系统能耗具有显著非线性影响，存在最优组合，可同时实现高效加热与低能耗运行；此外，研究提出了综合评估指标“加热质量系数”（ηq），证实DFNSE在加热效率、温度均匀性及系统经济性方面均优于传统笛形管，这一系数为防冰系统的性能评估提供了量化指标。该研究为航空发动机唇口防冰系统的优化设计提供了理论依据与工程指导。
This study addresses the anti-icing issue of the lip of a high-bypass turbofan engine. A numerical simulation method is employed to compare and analyze the heating performance of two bleed air anti-icing methods: the Directed Flow Nozzle Swirl Enhancer (DFNSE) and the traditional piccolo tube. The influence of key geometric parameters of the DFNSE (twist angle, number of flow channels, and contraction-expansion ratio of the annular flow passage) on the anti-icing effect is systematically investigated. The results indicate that, under identical bleed air conditions, the DFNSE exhibits a higher average temperature on the outer skin, lower bleed air pressure, and reduced thermal accumulation compared to the piccolo tube, resulting in a less-er impact on engine performance. Through numerical simulations of heat transfer effects under varying structural parameters, it is found that the twist angle, number of flow channels, and contraction-expansion ratio have significant nonlinear effects on heating uniformity and system energy consumption. An optimal combination exists, enabling both efficient heating and low-energy operation. Furthermore, the study pro-poses a comprehensive evaluation metric, the "heating quality coefficient" (ηq), which confirms that the DFNSE outperforms the traditional piccolo tube in terms of heating efficiency, temperature uniformity, and system economy. This coefficient provides a quantitative indicator for evaluating the performance of anti-icing systems. The research offers theoretical foundations and engineering guidance for the optimal de-sign of anti-icing systems for aero-engine lips.
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