直升机用高转速、小流量轴流风扇设计

Design of a High Rotating Speed,Low Flow Rate Axial Flow Fan Used on Helicopters

小流量、高转速、小尺寸轴流风扇的设计是高性能直升机滑油冷却系统的关键技术之一。针对直升机用轴流风扇的特点,进行了基本结构型式的分析和参数的优化计算;采用简化的三元流动设计理论得到叶轮叶片气动设计径向平衡方程式和求解约束条件,进而引入了控制涡设计理论进行风扇叶片造型,获得了优良的气动性能;采用“改进损失模型”的效率计算方法,为叶片气动方案的优化选择提供了理论依据。应用于某型号直升机用滑油冷却轴流风扇的设计计算,所得结果与试验结果吻合较好。

In the oil cooling system of a high performance helicopter,the low mass flow, high rotating speed and small size axial flow fan design is a key task. This special fan＇s structure was analyzed,and optimization of the relevant parameters was conducted. To obtain good aerodynamic characteristics,the radial aerodynamic balance equations were adopted to build the fan＇s rotating blades, which were evolved from the simplified three dimensional flow theories, the constraint conditions and the control vortex theory. The improved loss computing method was used to calculate the fan＇s efficiency,and to optimize design schemes. There is a good agreement between the design results and the experimental data while the design method is applied to an axial flow fan design for a helicopter.