基于横流风扇技术的直升机反扭验证

杜思亮; 吉孟江; 唐正飞; 陈仁良

doi:10.13700/j.bh.1001-5965.2016.0394

基于横流风扇技术的直升机反扭验证

doi: 10.13700/j.bh.1001-5965.2016.0394

杜思亮^{1, 2},
吉孟江¹,
唐正飞¹,
陈仁良^1, ,

1.
南京航空航天大学直升机旋翼动力学国家级重点实验室, 南京 210016
2.
淮阴工学院机械与材料工程学院, 淮安 223003

基金项目: 江苏高校优势学科建设工程资助项目

详细信息

作者简介:
杜思亮，男，博士。主要研究方向：飞行器空气动力学、飞行力学与控制

吉孟江，男，硕士研究生。主要研究方向：直升机空气动力学

唐正飞，男，博士，副教授，硕士生导师。主要研究方向：直升机空气动力学

陈仁良，男，博士，教授，博士生导师。主要研究方向：飞行力学与控制、直升机空气动力学

通讯作者:
陈仁良, E-mail: crlae@nuaa.edu.cn

中图分类号: V211.52
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出版历程
- 收稿日期: 2016-05-11
- 录用日期: 2016-06-24
- 网络出版日期: 2017-05-20

Helicopter anti-torque verification based on cross flow fan technology

1.
National Key Laboratory of Rotorcraft Aeromechanics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2.
Faculty of Mechanical & Material Engineering, Huaiyin Institute of Technology, Huaian 223003, China

Funds: Project Funded by the Priority Academic Program Development of Jiangsu Higher Education Institutions

More Information

Corresponding author: CHEN Renliang, E-mail:crlae@nuaa.edu.cn

摘要

摘要:
为了提高单旋翼带尾桨直升机的低空飞行安全性，利用横流风扇流动控制技术，设计了一种可以替代单旋翼直升机尾桨的反扭装置。通过风洞试验验证了该装置具有产生侧向力的特性，同时建立了该装置的数值模拟计算方法，得出了横流风扇转速、旋翼下洗流和前飞来流对该反扭装置的气动特性影响较大，初步分析了该反扭装置的侧向力的来源，证明了可以通过控制横流风扇转速来控制反扭装置侧向力的大小，因此应用于直升机的反扭系统是可行的。
- 直升机 /
- 反扭 /
- 横流风扇 /
- 风洞试验 /
- 计算流体力学(CFD)
Abstract:
In order to improve the safety of low altitude flight for the helicopter with tail rotor, an alternative anti-torque device has been proposed by using the flow control technology of the cross flow fan. Wind tunnel tests show that the device has the characteristics of lateral force. At the same time, the numerical simulation calculation method of the device has been established. It is concluded that the influence of the cross flow fan rotating speed, the rotor down wash flow and the front flying flow on the aerodynamic characteristics of the anti-torque device is great. The source of the force of the anti-torque device is analyzed. It is proved that the lateral force can be controlled by controlling the speed of cross flow fan and this device can be used as anti-torque device for helicopter.
- helicopter /
- anti-torque /
- cross flow fan /
- wind tunnel test /
- computational fluid dynamics (CFD)

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图 1 低速开口回流式风洞

Figure 1. Low velocity open flow wind tunnel

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图 2 试验反扭装置几何参数

Figure 2. Geometric parameters of test anti-torque device

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图 3 反扭装置在风洞位置

Figure 3. Location of anti-torque device in wind tunnel

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图 4 旋翼拉力随总距的变化曲线

Figure 4. Variation curves of rotor pulling force with collective pitch

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图 5 静止状态下不同叶片数量时侧向力和需用功率随转速的变化曲线

Figure 5. Variation curves of lateral force and required power with rotating speed under influence of different number of blades at stationary state

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图 6 静止状态下不同叶片安装角时侧向力和需用功率随转速的变化曲线

Figure 6. Variation curves of lateral force and required power with rotating speed under influence of different installation angle of blades at stationary state

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图 7 悬停状态下不同旋翼总距时侧向力和需用功率随转速的变化曲线

Figure 7. Variation curves of lateral force and required power with rotating speed under influence of different collective pitch at hover state

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图 8 前飞状态下不同旋翼总距时侧向力和需用功率随转速的变化曲线(前飞速度为5 m/s)

Figure 8. Variation curves of lateral force and required power with rotating speed under influence of different collective pitch at forward flight state (The forward flight speed is 5 m/s)

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图 9 前飞状态下不同旋翼总距时侧向力和需用功率随转速的变化曲线(前飞速度为10 m/s)

Figure 9. Variation curves of lateral force and required power with rotating speed under influence of different collective pitch at forward flight state (The forward flight speed is 10 m/s)

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图 10 计算域划分图

Figure 10. Calculation domain partition graph

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图 11 网格交界面图

Figure 11. Interface diagram of grid

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图 12 网格划分示意图

Figure 12. Schematic diagram of grid partition

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图 13 叶片安装角为10°时侧向力和需用功率随转速的变化曲线

Figure 13. Variation curves of lateral force and required power with rotating speed wheninstallation angle of blade is 10°

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图 14 叶片安装角为20°时侧向力和需用功率随转速的变化曲线

Figure 14. Variation curves of lateral force and required power with rotating speed wheninstallation angle of blade is 20°

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图 15 开口角为110°时侧向力和需用功率随转速的变化曲线

Figure 15. Variation curves of lateral force and required power with rotating speed when opening angle is 110°

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图 16 开口角变化时侧向力和需用功率随转速的变化曲线

Figure 16. Variation curves of lateral force and required power with rotating speed when opening angle changes

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图 17 接口对侧向力的影响曲线

Figure 17. Effect curves of interface on lateral force

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图 18 接口变化流线图

Figure 18. Streamlines of interface changes

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图 19 前飞速度为5 m/s时侧向力和需用功率随转速的变化曲线

Figure 19. Variation curves of lateral force and required power with rotating speed when forward flight speed is 5 m/s

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图 20 前飞速度为10 m/s时侧向力和需用功率随转速的变化曲线

Figure 20. Variation curves of lateral force and required power with rotating speed when forward flight speed is 10 m/s

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图 21 反扭装置内部流场速度矢量图

Figure 21. Internal flow field velocity vector diagram of anti-torque device

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图 22 反扭装置内部流场速度云图

Figure 22. Internal flow field velocity contours of anti-torque device

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表 1 试验风洞参数

Table 1. Parameters of test wind tunnel

参数	数值
测试区尺寸/(m×m)	3.4×2.4
最大风速/(m·s^-1)	40
最小稳定风速/(m·s^-1)	5
收缩比	4

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表 2 几何参数定义

Table 2. Definition of geometric parameters

参数	数值
开口角度ψ/(°)	90，110，130，150
横流风扇外圆半径R₁/mm	100
横流风扇出口高度ζ/mm	45
叶片安装角γ/(°)	0，10，20，30
叶片弦长C/mm	25
叶片数量/片	10，12，14，16
叶片长度/mm	500
横流风扇与壳体间隙σ/mm	5

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表 3 旋翼台参数

Table 3. Parameters of rotor bench

参数	数值
桨叶片数/片	4
桨叶半径/m	1.25
桨叶弦长/m	0.072
几何扭转角度/(°)	0
旋翼实度	0.077
桨叶翼型	NACA 0012

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