悬停状态下分布式涵道风扇气动干扰规律分析

吴正园; 陈新民; 熊俊辉; 杨旭东; 陆佳南

doi:10.13224/j.cnki.jasp.20240673

悬停状态下分布式涵道风扇气动干扰规律分析

doi: 10.13224/j.cnki.jasp.20240673

吴正园^{1, 2,},
陈新民^2,*, ,,
熊俊辉^{1, 2},
杨旭东³,
陆佳南^{1, 2}

1.
宁波杭州湾新材料研究院，浙江宁波 315336
2.
中国科学院宁波材料与工程技术研究所，浙江宁波 315336
3.
西北工业大学航空学院，西安 710072

基金项目: 宁波市2025重大攻关项目（2022Z040）

详细信息

作者简介:
吴正园（1992-），男，助理研究员，博士，研究领域为空气动力学和CFD

通讯作者:
陈新民（1972-），男，研究员，博士，研究领域为导弹总体设计、飞行器总体设计。E-mail：chenxinmin@nimte.ac.cn

中图分类号: V211
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- 被引次数: 0
出版历程
- 收稿日期: 2024-09-30
- 网络出版日期: 2026-04-22

Study on aerodynamic interaction phenomenon among distributed ducted fans under hovering condition

Wu Zhengyuan^{1, 2
,},
Chen Xinmin^{2,*
, ,},
Xiong Junhui^{1, 2},
Yang Xudong³,
Lu Jianan^{1, 2}

1.
Qianwan Institute of CNITECH，Ningbo Zhejiang 315336，China
2.
Ningbo Institute of Materials Technology and Engineering，Chinese Academy of Sciences，Ningbo Zhejiang 315336，China
3.
School of Aeronautics，Northwestern Polytechnical University，Xi’an 710072，China

摘要

摘要:
为进一步探究分布式涵道风扇间的气动干扰现象，开展了涵道风扇单元和不同布局分布式涵道风扇组的地面试验或数值模拟研究。结合地面试验和CFD数值模拟，发现在静态条件下，所研制的100 kg推力级别涵道风扇单元的涵道部件可提供与桨叶部件相当的推力。用CFD方法研究了并列式涵道风扇组和融合式涵道风扇组的气动干扰机理，总结气动干扰对涵道和桨叶等部件的推力性能的影响规律。研究发现：气动干扰诱导涵道入口速度场畸变，使涵道前缘唇口表面压强分布不均匀，引起各涵道前缘毗邻区域压强升高，导致涵道前缘吸力减小。但另一方面，气动干扰使涵道尾缘压强升高，致使尾缘推力小幅增加。对桨叶部件，气动干扰使得中间位置涵道风扇桨叶诱导气流速度略微减小，桨叶实际攻角稍增大，桨叶推力略增大。综合涵道风扇组气动干扰对涵道和桨叶各自的作用规律，发现并列式涵道风扇组的平均推力相比涵道风扇单元几乎不变，而力效略微下降。另外，三涵道风扇组的桨叶旋转方向布置对其推力性能的影响很小。对融合涵道风扇组，涵道前缘唇口外形变化和尾缘流动分离使涵道部件的推力明显降低，融合式设计未能取得涵道风扇组气动性能的提升。
- 涵道风扇 /
- 分布式推进 /
- 气动干扰 /
- 气动布局 /
- 地面试验 /
- 计算流体力学
Abstract:
To further investigate the aerodynamic interaction phenomenon among distributed ducted fans, ground tests or numerical simulation studies of ducted fan unit and distributed ducted fans with different configuration were carried out. Combining ground test and CFD numerical simulation, it was found that under static conditions, for a 100 kg-class ducted fan unit, more than half of the total thrust was generated by the duct, while the rest of thrust was mainly provided by the rotor. Based on CFD simulations, the aerodynamic interaction mechanism of two different types of distributed ducted fan configurations was investigated. Focusing on the thrust performance of duct and blade under aerodynamic interaction, the velocity and pressure fields from the leading edge to the trailing edge were analyzed. It showed that the wall pressure increased significantly near the leading edge due to strong aerodynamic interaction with the adjacent duct. Concurrently, the induced flow velocity around the leading edge decreased rapidly compared with the isolated ducted fan, leading to a substantial reduction in duct thrust. Meanwhile, the wall pressure at the trailing edge also increased, owing to the decrease of flow velocity at the outlet of duct. The thrust of rotor raised slightly due to the increase of the actual angle of attack of blade. Eventually, the average thrust of ducted fan group remained almost unchanged compared with that of the ducted fan unit. In addition, the blade rotation direction of the three ducted fans had little effect on thrust performance. For the integrated ducted fan set, the change of duct leading edge shape led to obvious reduction on thrust. Besides, flow separation at trailing edge region of integrated ducted fan also resulted in lower wall pressure compared with ducted fan unit, bringing down the thrust of duct furthermore. As a conclusion, current integrated design concept does not lead to an improvement in the aerodynamic performance of the ducted fan set.
- ducted fan /
- distributed propulsion /
- aerodynamic interaction /
- aerodynamic configuration /
- ground test /
- computational fluid dynamic

HTML

图 1 地面试验台和样机

Figure 1. Ground test bench and prototype

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图 2 涵道风扇外形

Figure 2. Shape of ducted fan

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图 3 MRF方法计算域设置

Figure 3. Computation domain setup of MRF method

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图 4 涵道风扇总推力与转速的对应关系

Figure 4. Relation of ducted fan total thrust with respect to rotation speed

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图 5 轴功率与总推力的关系曲线

Figure 5. Curve of axial power with respect to total thrust

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图 6 涵道风扇表面压强云图

Figure 6. Wall pressure contour of ducted fan

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图 7 涵道风扇单元z=0 m截面内的V_x云图

Figure 7. V_x contour at z=0 m plane of ducted fan unit

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图 8 涵道与桨叶推力的占比与转速的关系

Figure 8. Relation between the ratio of duct and blade thrust with rotation speed

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图 9 20 mm间隔下涵道风扇旋转方向分布

Figure 9. Distribution of ducted fan rotation directions under the gap of 20 mm

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图 10 20 mm间距下z=0 m截面内的V_x云图

Figure 10. V_x contour at z=0 m plane under the gap of 20 mm

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图 11 20 mm间距下x=0.8 m截面内的流线

Figure 11. Streamlines at x=0.8 m plane under the gap of 20 mm

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图 12 D1布局下涵道风扇表面压强云图

Figure 12. Wall pressure contour of ducted fans under D1 configuration

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图 13 涵道前缘和后缘处的压强结果对比

Figure 13. Comparison of wall pressure at the leading and trailing edges of ducted fan

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图 14 涵道后缘处V_x沿y轴的分布对比

Figure 14. Distribution of V_x along y-direction at the trailing edges of ducted fan

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图 15 D1布局下涵道风扇旋转方向分布

Figure 15. Distribution of ducted fan rotation directions under D1 configuration

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图 16 D1布局下涵道风扇后缘处表面压强结果对比

Figure 16. Comparison of wall pressure at the trailing edges of ducted fan under D1 configuration

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图 17 涵道风扇融合构型

Figure 17. Merged shape of ducted fans

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图 18 融合构型前缘处表面压强云图

Figure 18. Wall pressure contour at the leading edge of merged shape

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图 19 融合构型涵道后缘处压强云图

Figure 19. Wall pressure contour at the trailing edge of merged shape

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表 1 涵道风扇主要参数

Table 1. Main parameter of ducted fan

参数	数值
桨叶片数	6
涵道直径/mm	600
支臂片数	6
桨叶桨尖弦长/mm	60
总距角/（°）	32
涵道长度/mm	300

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表 2 网格无关性分析计算设置

Table 2. Computational setup of grid-independent analysis

网格参数	M1	M2	M3
网格点数 /10⁶	8.1	11.0	14.5
Δy₁/mm	0.016	0.016	0.006
边界层网格层数	25	25	30
边界层网格增长率	1.25	1.20	1.15

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表 3 不同网格下的计算结果对比

Table 3. Comparison of computational results across different meshes

参数	M1	M2	M3
转速/（r/min）	7400	7400	7400
总推力/N	1090	1088	1094
桨叶推力/N	507	504	510
涵道推力/N	562	560	568
支臂推力/N	27	30	28
桨毂推力/N	−6	−9	−12
总力效	2.39	2.41	2.41

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表 4 D20间距下的推力结果

Table 4. Thrust results of D20 configuration

参数	涵道风扇单元	并列式布局-D20
参数	涵道风扇单元	左	中	右
总推力/N	1180	1184	1149	1205
桨叶推力/N	569	569	584	576
涵道推力/N	571	570	516	589
支臂推力/N	34	35	39	31
桨毂推力/N	6	10	10	9
轴功率/kW	55	55	56	58
力效	2.19	2.20	2.11	2.13

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表 5 D1间距布局下的推力结果

Table 5. Thrust results under D1 configuration N

参数	涵道风扇单元	并列式布局-D1
参数	涵道风扇单元	左	中	右
总推力	1180	1195	1156	1196
桨叶推力	569	563	582	564
涵道推力	571	588	525	590
支臂推力	34	34	40	34

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表 6 D1R2布局推力结果对比

Table 6. Thrust results of D1R2 configuration N

参数	D1R2
参数	左	中	右
总推力	1200	1156	1203
桨叶推力	578	578	577
涵道推力	592	530	583
支臂推力	34	40	34

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表 7 D1R3布局推力结果对比

Table 7. Thrust results of D1R3 N

参数	D1R3
参数	左	中	右
总推力	1208	1157	1208
桨叶推力	588	585	573
涵道推力	581	525	580
支臂推力	36	38	36

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表 8 融合构型推力结果

Table 8. Thrust results of merged configuration

参数	涵道风扇单元	融合构型
参数	涵道风扇单元	左	中	右
总推力/N	1180	1130	1073	1131
桨叶推力/N	569	554	561	556
涵道推力/N	571	532	468	531
支臂推力/N	34	31	32	31
力效	2.19	2.13	2.01	2.13

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