30kW级航空电驱动涵道风扇设计与试验

30kW Aviation Electric Drive Ducted Fan Design and Experiment

为适应未来航空电气化的发展需求,研究了30kW级航空电驱动涵道风扇设计方法。涵道风扇性能设计基于航空发动机压缩部件设计流程。以推进系统总体性能为设计目标,完成了转子、流道以及短舱的气动外形设计。对各组成部件建立性能分析模型,评估全工况范围特性。涵道风扇结构设计采用风扇-电机一体化设计思想,简化连接方式的同时减少零件数。采用航空发动机结构强度分析方法,对涵道风扇各部件的应力、振动等特性进行评估分析。完成了30kW涵道风扇试制并开展地面和飞行试验研究。按照航空发动机整机试验方法,在整机试验台架完成涵道风扇地面性能试验。通过对比分析,试验结果与设计值误差在5%以内,验证了设计方法的有效性与正确性。涵道风扇配装轻型通航飞机完成了飞行试验,全系统工作正常,进一步验证了实际使用环境下涵道风扇的工作可靠性。

In order to meet the future development needs of aviation electrification, 30kW aviation electric drive ducted fan is studied. The performance design of ducted fan is carried out based on the existing design method of aircraft engine compressor. The rotor, flowpath and nacelle aerodynamic configuration is designed to satisfy the propulsion system overall performance. The performance analysis model is established to evaluate the characteristic of full work conditions. The ducted fan structure design adopted the fan-motor integrated design method.The connection mode is simplified and the number of parts is reduced. The stress and vibration performance of each part of ducted fan is analyzed based on the strength analysis method of aircraft engine. The 30kW ducted fan is manufactured and ground and flight test is also carried out. The ground test is carried out on the aircraft engine test facility. The error between design value and test results is less than 5%. The effectiveness and correctness of ducted fan design method is validated. The flight test of ducted fan is carried out on a general aviation aircraft. All system works properly, which demonstrated the reliability of ducted fan in actual operating environment.