侧流对平流层飞艇螺旋桨气动载荷的影响

聂波; 王海峰; 杜晨曦; 马界祥

doi:10.13224/j.cnki.jasp.20230207

侧流对平流层飞艇螺旋桨气动载荷的影响

doi: 10.13224/j.cnki.jasp.20230207

1.
西北工业大学航空学院，西安 710072
2.
中国航空工业集团有限公司第一飞机设计研究院，西安 710089

详细信息

作者简介:
聂波（1999-），男，硕士生，主要从事飞行器总体设计研究。E-mail：nbnwpu@163.com

中图分类号: V211
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- 被引次数: 0
出版历程
- 收稿日期: 2023-04-01
- 网络出版日期: 2024-04-05

Impact of cross-flow on the aerodynamic load of propeller for stratospheric airship

1.
School of Aeronautics，Northwestern Polytechnical University，Xi’an 710072，China
2.
The First Aircraft Institute，Aviation Industry Corporation of China，Limited，Xi’an 710089，China

摘要

摘要:
利用滑移网格技术和脱体涡模拟（DES）的非定常数值方法，采用螺旋桨缩比模型风洞试验验证了方法的有效性，完成了不同侧流状态下气动载荷数值计算。结果表明：螺旋桨旋转的瞬时气动载荷系数呈现周期性的非定常特性，沿桨叶径向的挥舞力矩随侧流偏角递增明显，在30°侧流偏角时瞬时值与轴向力矩相当，60°时超过轴向力矩2倍；随桨叶数增多，一个周期内的波动频率增加，四叶桨拉力和扭矩系数相对时均值的波动幅度比两叶桨分别缩减了76.6%和70.1%。所研究方法可为桨叶结构和相关支撑机构的设计提供有效的输入依据。
- 侧流 /
- 平流层飞艇 /
- 螺旋桨 /
- 滑移网格 /
- 脱体涡模拟 /
- 非定常
Abstract:
The validity of sliding mesh technology and detached eddy simulation (DES) with non-steady numerical methods was verified by wind tunnel tests of a scaled propeller model, and numerical calculations of aerodynamic loads under different cross-flow conditions were performed. The results showed that the instantaneous aerodynamic load coefficient of the rotating propeller exhibited periodic unsteady characteristics, and the flapping torque along the blade radius increased significantly with cross-flow angle, with an instantaneous value equivalent to the axial moment at 30°, and more than twice the axial moment at 60°. Along with an increasing number of blades, the frequency of fluctuations within one cycle increased. Compared with the two-bladed propeller, the amplitude of the thrust and torque coefficients of the four-bladed propeller relative to their mean values was reduced by 76.6% and 70.1%, respectively. Research method can provide effective input basis for the design of blade structure and related support mechanism.
- cross-flow /
- stratospheric airship /
- propeller /
- sliding mesh /
- detached eddy simulation /
- unsteady

HTML

图 1 飞艇推进系统布局

Figure 1. Airship propulsion system layout

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图 2 螺旋桨侧流状态示意图

Figure 2. Cross-flow state of propeller

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图 3 CFD模拟流场网格图

Figure 3. CFD simulation of flow field

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图 4 网格无关性验证

Figure 4. Mesh independence verification

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图 5 风洞试验示意图

Figure 5. Wind tunnel test

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图 6 D=1.0 m木制缩比螺旋桨

Figure 6. D=1.0 m wooden shrink propeller

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图 7 拉力系数的试验值与计算值对比

Figure 7. Comparison of thrust coefficient between calculation and experiment

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图 8 扭矩系数的试验值与时均计算值对比

Figure 8. Comparison of torque coefficient between calculation and experiment

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图 9 效率的试验值与时均计算值对比

Figure 9. Comparison of efficient between calculation and experiment

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图 10 不同侧流角下拉力系数与转速关系

Figure 10. Relationship between thrust coefficient and rotation speed at different cross-flow angles

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图 11 不同侧流角下扭矩系数与转速关系

Figure 11. Relationship between moment coefficient and rotation speed at different cross-flow angles

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图 12 叶素速度矢量合成示意图

Figure 12. Airfoil velocity vector synthesis

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图 13 推力系数随前进速度的变化

Figure 13. Thrust coefficient with cross-flow velocity

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图 14 力矩系数随前进速度的变化

Figure 14. Moment coefficient with cross-flow velocity

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图 15 推力系数与相位角关系

Figure 15. Thrust coefficient with phase angle

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图 16 力矩系数与相位角关系

Figure 16. Moment coefficient with phase angle

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图 17 不同相位角下桨叶压力分布与旋转平面速度云图

Figure 17. Blade pressure distribution and rotation plane velocity cloud map at different phase angles

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图 18 挥舞力矩与轴向力矩的比值随相位角变化关系

Figure 18. Ratio of flapping moment to axial moment with phase angle

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图 19 推力特性随相位角变化关系

Figure 19. Thrust characteristics with phase angle

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图 20 力矩特性随相位角变化关系

Figure 20. Moment characteristics with phase angle

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表 1 试验值与计算值的最大相对误差

Table 1. Maximum relative error between calculation and experiment

气动性能	最大相对误差/%
气动性能	SST k-ω模型	DES模型
拉力系数	8.67	4.27
扭矩系数	4.92	2.69
效率/%	9.51	3.79

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表 2 单个周期内的气动载荷系数

Table 2. Aerodynamic load coefficient within one cycle

载荷系数	最大值	时均值	最小值
C_Tx	0.06639	0.06561	0.06464
C_Ty	1.20×10⁻⁴	7.79×10⁻⁷	−1.20×10⁻⁴
C_Tz	0.00367	2.25×10⁻⁵	−0.00367
C_Mx	0.00532	0.00528	0.00523
C_My	7.01×10⁻⁵	2.22×10⁻⁷	−7.00×10⁻⁵
C_Mz	0.00525	2.42×10⁻⁵	−0.00527

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