为提高防冰性能评估效率，更好地支撑发动机短舱防冰系统设计工作，基于松散耦合方法开展了适用于短舱进气道笛形管防冰系统的三维内外流耦合仿真计算方法研究。将三维全尺寸短舱进气道计算模型分割为内、外流计算域，并以防冰腔外表面温度和换热系数作为计算域之间的交互数据，以实现内外流耦合迭代。根据干、湿空气条件下防冰表面流动传热特性，考虑湿空气条件下由过冷水滴撞击产生的质量与能量源项，同时引入短舱进气道周向非对称特性导致的三维溢流效应影响，总结了干、湿空气条件下短舱进气道防冰系统内外流松散耦合迭代策略。计算结果表明：在干空气条件下防冰内外流松散耦合迭代仅需3个轮次即可收敛；在湿空气条件下，受防冰表面溢流影响，内外流耦合迭代4个轮次后趋于收敛。

To improve the efficiency of anti-icing performance evaluation and support the design of nacelle anti-icing system， a 3D computational method for conjugate heat transfer between internal and external flow of the nacelle inlet piccolo hot air anti-icing system is proposed based on the loose-coupling method. The external flow field， skin solid domain and internal flow field in the 3D nacelle model are divided into two computational domains. The wall temperature and heat transfer coefficient on the external surface of anti-icing chamber are taken as the interactive data between the internal and external domains to realize conjugate computation. According to the flow and heat transfer characteristics on the anti-icing surface under the dry and wet air conditions， the mass and energy source terms generated by supercooled water droplet impingement and the 3D runback effect caused by the circumferential asymmetry of nacelle inlet are considered， and the loose-coupling iterative strategies for the dry and wet air conditions are summarized. The results show that under the dry air condition， the calculation of conjugate heat transfer between internal and external flow can converge in 3 rounds of loose-coupling iteration； under the wet air condition， the calculation for nacelle inlet inner surface tends to converge after 4 rounds of iteration.