针对仿制重构方法的逆向设计很难满足新型航空发动机预旋供气系统性能要求，本文提出基于正向设计的原创维度，从设计点参数出发，建立了预旋供气系统正向设计框架，采用叶孔式预旋喷嘴与斜接受孔，通过一维计算获得了预旋供气系统设计点沿程特征截面的气动参数、特征元件的具体几何结构参数及初步预测系统温降性能，并对一维设计结果进行三维校核。开展基于正向设计的预旋供气系统流动温降特性的性能改进评估，重点揭示接受孔入口气流攻角对系统性能的影响规律。研究表明：预旋供气系统一维设计与三维计算的流量平均偏差仅为0.8%，系统温降效率的平均偏差仅为5.12%；综合熵增、温降、功耗等系统各个性能参数，接受孔入口气流的性能平稳攻角范围为-7°~3°，由此说明基于正向设计方法对提升系统性能具有可行性。叶孔式预旋喷嘴流量系数高出孔式预旋喷嘴10.63%，高出叶片式预旋喷嘴4.58%；采用斜接受孔后，转子部分流动损失减小，区域阻力降低。正向设计得到的低位预旋供气系统的温降效率为66%，相较于低位预旋供气系统整体水平，温降效率提升45.2%以上。

Given that it is difficult for reverse design of imitation reconstruction method to meet the performance requirements of the advanced aero-engine pre-swirl system， this paper proposes an original forward design framework. Starting from design point parameters， the framework establishes a forward design process for the pre-swirl system， adopting the vane shaped hole nozzle and oblique receiver hole. Through one-dimensional design calculation， the aerodynamic parameters along the characteristic cross-section at the design point of the pre-swirl system， the specific geometrical structural parameters of the characteristic components， are obtained， along with a preliminary prediction of the system temperature drop performance. The results of one-dimensional design are then calibrated through three-dimensional calculation. The performance improvement evaluation of the flow and temperature drop characteristic of the pre-swirl system based on forward design is carried out， with emphasis on revealing the influence of the angle of attack of the airflow at the inlet of the receiver hole on the performance of the system. The study shows that the average deviation of the flow rate between the one-dimensional design and the three-dimensional calculation of the pre-swirl system is only 0.8%， and the average deviation of the system temperature drop efficiency is only 5.12%. Combining the entropy increase， temperature drop， power consumption， and other performance parameters of the system， the range of angle of attack at the inlet of the receiver hole when the system performance parameters are stable is-7° to 3°， indicating that it is feasible to improve the performance of the system based on the forward design method. The discharge coefficient of the vane shaped hole pre-swirl nozzle is 10.63% higher than that of the hole-type nozzle， and 4.58% higher than that of the cascade vane nozzle. The results also show that flow loss in the rotating zone is reduced by using oblique receiver holes， and the area resistance is lowered. The temperature drop efficiency of the low-radius pre-swirl system designed by the forward design method is 66%， which is more than 45.2% higher compared to the overall level of the low-radius pre-swirl system.