分布式涵道风扇气动布局复杂强干扰效应及性能影响

doi:10.7527/S1000-6893.2024.30805

Abstract

Abstract:

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 vehicle. Using CFD numerical simulation and ground test， this paper studies the aerodynamic configurations and parameter 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 number of ducted fans， and the influence of the jet flow on the propulsion performance of the ducted fan groups are analyzed 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.

Key words: ducted fan, distributed electric propulsion vehicle, aerodynamic coupling interference, ground effect, propulsion efficiency

CLC Number:

V211

Zhuoyuan LI, Xudong YANG, Kai SUN, Junhui XIONG, Shuai SHI. Aerodynamic configuration of distributed ducted fan with complex strong interference effect and performance influence[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(3): 130805.

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涵道位置	总推力系数	总功率系数	力效/（kg·kW^-1）	质量流量/（kg·s^-1）
左涵道风扇	0.889 4	0.629 3	2.403 5	16.025 0
中涵道风扇	0.864 2	0.634 3	2.317 1	15.866 4
右涵道风扇	0.890 4	0.629 2	2.406 6	16.028 8
单元涵道风扇	0.893 4	0.628 3	2.418 4	16.325 4

涵道位置	桨叶推力系数	涵道推力系数	消旋定子推力系数
左涵道风扇	0.423 7	0.442 3	0.019 3
中涵道风扇	0.428 9	0.410 8	0.019 8
右涵道风扇	0.423 2	0.443 8	0.019 3
单元涵道风扇	0.421 6	0.446 8	0.019 1

涵道位置	总推力系数	功率系数	力效/（kg·kW^-1）	力效变化量/%
左涵道风扇	0.882 5	0.651 5	2.303 8	-4.74
中涵道风扇	0.855 7	0.648 3	2.245 0	-7.17
右涵道风扇	0.864 9	0.627 5	2.343 8	-3.08
涵道风扇组	2.603 1	1.927 3	2.297 0	-5.02
单元涵道风扇	0.893 4	0.628 3	2.418 4

涵道位置	桨叶推力系数	涵道推力系数	定子推力系数
左涵道风扇	0.449 0	0.410 3	0.014 5
中涵道风扇	0.444 1	0.386 1	0.016 8
右涵道风扇	0.424 3	0.416 5	0.015 5
涵道风扇组	1.317 4	1.212 9	0.046 8
单元涵道风扇	0.421 6	0.446 8	0.019 1

涵道位置	总推力系数	功率系数	质量流量（kg·s^-1）	力效/（kg·kW^-1）
左涵道风扇	0.847 7	0.672 8	14.192 3	2.142 9
中涵道风扇	0.812 3	0.660 6	12.582 0	2.091 4
右涵道风扇	0.820 1	0.657 7	13.091 9	2.120 8
涵道风扇组	2.480 1	1.991 1	39.866 2	2.118 5

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

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涵道位置	桨叶推力系数	涵道推力系数	定子推力系数
左涵道风扇	0.504 2	0.314 1	0.019 3
中涵道风扇	0.530 8	0.244 5	0.016 8
右涵道风扇	0.515 8	0.272 6	0.020 4
涵道风扇组	1.550 8	0.831 2	0.056 5

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