分布式涵道风扇气动布局复杂强干扰效应及性能影响  

Aerodynamic configuration of distributed ducted fan with complex strong interference effect and performance influence

作　　者：李卓远 杨旭东[1,2] 孙恺 熊俊辉 史帅 LI Zhuoyuan;YANG Xudong;SUN Kai;XIONG Junhui;SHI Shuai(School of Aeronautics,Northwestern Polytechnical University,Xi’an 710072,China;National Key Laboratory of Aircraft Configuration Design,Xi’an 710072,China;Ningbo Institute of Materials Technology&Engineering,Chinese Academy of Sciences,Ningbo 315201,China)

机构地区：[1]西北工业大学航空学院,西安710072 [2]飞行器基础布局全国重点实验室,西安710072 [3]中国科学院宁波材料技术与工程研究所,宁波315201

出　　处：《航空学报》2025年第3期218-237,共20页Acta Aeronautica et Astronautica Sinica

基　　金：宁波市2025重大攻关项目(2022Z040)。

摘　　要：分布式涵道风扇动力系统被认为是下一代民机设计最具有发展潜力的动力系统之一,多个涵道风扇之间(涵道风扇组),涵道风扇组与机翼/襟翼之间等复杂气动耦合干扰特性与推进性能影响规律制约着新概念分布式电推进飞行器的发展。采用CFD数值模拟和地面试验验证相结合的研究手段,重点开展了单元涵道风扇、涵道风扇组、涵道风扇组与机翼襟翼等分布式涵道风扇构型气动布局形式和参数影响机理研究,从非融合涵道风扇组间距、融合涵道风扇组外形、涵道风扇数量、涵道风扇组地面尾流对推进性能影响等方面,阐释了分布式涵道动力系统在悬停、垂直起降状态下不同构型对推进效率、推力分布及桨叶载荷等的影响关系。研究表明:分布式涵道风扇动力布局对力效影响为3%~5%,横向紧凑布置的分布式涵道风扇会导致相邻涵道之间的入涵气流迎角减小,降低推进力效,内侧涵道受影响最为明显;涵道风扇组融合会引起入涵气流畸变,涵道顶部扩张段产生流动分离,导致力效降低;垂直起降阶段近地面尾流会增大桨叶推力和消耗功率,降低涵道推力,且内侧涵道受影响最明显。离地间距增加后,喷流影响逐渐减弱,力效损失减少。The distributed ducted fan power system is considered as one of the most potential power systems for the next generation civil aircraft design.The complex aerodynamic coupling between ducted fan group and wing/flap and the influence law of propulsion performance restricts the development of new concept distributed electric propulsion ve⁃hicle.Using CFD numerical simulation and ground test,this paper studies the aerodynamic configurations and param⁃eter influence mechanism of distributed ducted fans,such as the single ducted fan,ducted fan group,ducted fan group with flap.The distance between non-fusing ducted fan groups,the shape of fusing ducted fan groups,the num⁃ber of ducted fans,and the influence of the jet flow on the propulsion performance of the ducted fan groups are ana⁃lyzed to explore the effects of different configurations of distributed culvert power system on propulsion efficiency,thrust distribution and blade load in hover and vertical take-off and landing states.The results show that the influence of the dynamic configuration of distributed ducted fan on the propulsion performance is about 3%–5%.The transverse compact distributed ducted fan can reduce the angle of attack of the incoming air flow between adjacent ductwork and reduce the propulsion efficiency,and the inner culvert is affected most obviously.The convergence of culvert fan group causes the distortion of air flow into the culvert and the flow separation at the expansion section of the culvert top,resulting in reduction of force effect.In the vertical take-off and landing stage,the near-surface jet increases the blade thrust and consumes power and decreases the ducted thrust,and the inner ducted is affected most obviously.With the increase of the distance from the ground,the effect of jet decreases gradually and the loss of force decreases.

关 键 词：涵道风扇 分布式电推进飞行器 气动耦合干扰 地面效应 推进效率 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]