针对桨扇发动机全环形进气道，开展8X8对转桨扇与进气道的耦合气动影响研究，采用滑移网格进行非定常流场计算，对比分析了高空巡航状态和地面起飞状态两种典型工况下对转桨扇/进气道的耦合气动影响，归纳总结了不同工况下的滑流影响机理、定量影响结果以及对转桨扇耦合进气道前后的气动性能差异。研究结果表明：对转桨扇产生的桨毂涡是影响进气道内流特性的主要因素，巡航工况下后排尾迹涡是进气道内涡系结构的主导，是造成流动不均匀的主要因素，地面工况下前后排尾迹耦合增强，常以对涡形式存在，共同影响进气道内流流场。尾迹涡在进气道内从前向后周期性运动带来气动参数的周期性振荡，当进气道内涡系结构以桨扇尾迹涡为主时，进气道沿程参数振荡幅值逐渐衰减，但振荡频率保持不变，相位角也保持等间距落后，当壁面分离涡脱体后，进气道涡系结构发生变化，参数振荡幅值、频率以及相位角均因分离涡的掺混发生扰动。滑流使得进气道总压恢复系数有所增加，但复杂的尾迹涡导致进气道出口总压畸变和旋流畸变急剧恶化，内流出现严重不均匀分布，内流流动损失在巡航时增加大2.85倍，起飞时增大1.09倍。此外，耦合进气道后改变了对转桨扇不同高度叶素的工作特性，提高了桨扇推力性能，在设计工况下，前排桨叶推力系数提高了5.9%，后排推力系数提高了27%，桨扇整体效率提高了5.2%

A study was conducted on the aerodynamic interference effects of contra-rotating propfan(CRP) and propfan engine inlet. Unsteady numerical calculation was carried out by sliding grid method, and the coupled aerodynamic effects of the 8X8CRP and inlet were compared and analyzed under two typical operating conditions: high-altitude cruising state and ground takeoff state. The mechanism of slipstream effects and quantitative results on inlet under different condi-tions, and differences of CRP aerodynamic performance before and after coupled inlet were summarized. Results indicate that the hub vortex produced by the CRP is the primary factor influencing the flow characteristics within the intake duct. Under cruise condition, wake vortices of the rear row dominate the vortex structure of the inlet and cause non-uniform flowfield. Under takeoff condition, the coupling of wake vortices of both front and rear rows enhance , which leading to vortices exist in pairs. So that wake vortices of both front and rear rows collectively impact the flow field within the inlet. The periodic movement of wake vortices within the inlet induces periodic fluctuations in aerody-namic parameters. When propfan wake vortices dominate the vortex structure, the amplitude of parameter oscillations diminishes along the duct, yet the oscillation frequency remains constant and the phase angle maintains a uniform lag. Following the detachment of wall-separated vortices, the duct's vortex structure undergoes changes, disrupting the amplitude, frequency, and phase angle of parameter oscillations due to the mixing of these separated vortices. The slipstream enhances the intake duct's total pressure recovery coefficient; however, the intricate trailing vortices signifi-cantly exacerbate total pressure and swirl distortions at the duct's exit, leading to pronounced uneven internal flow distributions. Internal flow losses increase by 2.85 times during cruising and 1.09 times during takeoff. Additionally, integrating the intake duct alters the operational characteristics of blades at varying heights of the counter-rotating propeller fan, enhancing the fan's thrust performance. Under design conditions, the thrust coefficient of the front-row blades rose by 5.9%, that of the rear-row blades increased by 27%, and the propeller fan's overall efficiency improved by 5.2%