旋翼动态失速与反流流动控制研究进展

李国强; 赵鑫海; 易仕和; 宋奎辉; 赵光银

doi:10.11729/syltlx20230054

旋翼动态失速与反流流动控制研究进展

doi: 10.11729/syltlx20230054

李国强^{1, 2,},
赵鑫海^2, ,,
易仕和¹,
宋奎辉²,
赵光银²

1.
国防科技大学空天科学学院，长沙　410073
2.
中国空气动力研究与发展中心低速空气动力研究所，绵阳　621000

基金项目: 预先研究项目（50906030601）；综合研究项目（JK20211A020092）

详细信息

作者简介:
李国强：（1987—），男，安徽蚌埠人，硕士，工程师。研究方向：直升机空气动力学，主动流动控制技术。通信地址：四川省绵阳市涪城区二环路南段6号13 信箱（621000）。E-mail：CARDCL@126.com

通讯作者:
E-mail：18773129527@163.com

中图分类号: V211.4
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出版历程
- 收稿日期: 2023-04-13
- 修回日期: 2023-05-24
- 录用日期: 2023-05-26
- 网络出版日期: 2023-07-31
- 刊出日期: 2023-08-30

Research progress on rotor reverse flow and dynamic stall flow control methods

1.
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha　410073, China
2.
Low Speed Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang　621000, China

摘要

摘要: 直升机在大载荷高速前飞时，旋翼桨叶桨距变化较大，易发生动态失速；后行桨叶内段旋转线速度较低，在来流叠加下形成反流区，导致桨叶气动效率降低，由此产生的桨叶疲劳失效和升力下降问题阻碍直升机性能的进一步提升。流动控制方法在改善翼型气动特性方面具有较大潜能，是提升旋翼气动效率、保障直升机安全的有效路径之一。本文阐述了旋翼反流区和动态失速的形成机理及非定常流动特征，综述了2种特殊气动现象的研究成果。对比分析了优化翼型几何构型、添加表面机械结构、吹气控制、等离子体控制、合成射流控制和后缘小翼控制等流动控制方法对旋翼动态失速及反流控制的机理，总结了控制参数和流场参数对控制效果的影响规律，分析了各种方法在应用中存在的问题，对发展方向进行了展望。
- 旋翼 /
- 动态失速 /
- 反流 /
- 流动控制
Abstract: When a helicopter flies forward at high speed with heavy load, the blade pitch changes greatly and dynamic stall is prone to occur. The lower rotational speed of the inner section of the trailing blade leads to the formation of a reverse flow zone under the superposition of the incoming flow, resulting in a reduction in the aerodynamic efficiency of the blade. The problems of blade fatigue failure and lift reduction hinder the further improvement of helicopter performance. Flow control methods have great potential in improving the aerodynamic characte-ristics of airfoils, and are effective ways to improve the rotor aerodynamic efficiency and ensure helicopter safety and stability. In this paper, the formation mechanism and unsteady flow characteristics of the reverse flow zone and dynamic stall are firstly described, and the research results of two special aerodynamic phenomena are summarized. On this basis, a comparative analysis of flow control methods such as variable airfoil configuration, surface mechanical devices, air-blowing control, plasma actuator, synthetic jet actuator, and trailing edge flap on the mechanism of rotor dynamic stall and reverse flow control is conducted, and the effects of control parameters and flow field parameters on control effectiveness are summarized. Finally, the remain-ing problems and solutions in the application of various flow control methods are prospected.
- rotorcraft /
- dynamic stall /
- reverse flow /
- flow control

HTML全文

图 1 不同前进比对应的反流区示意图

Figure 1. Reverse region with different μ

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图 2 典型状态下直升机桨叶剖面阻力系数分布^[10]

Figure 2. Distribution of resistance coefficient of helicopter blade under typical conditions^[10]

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图 3 翼型俯仰运动对升力系数的影响^[14]

Figure 3. Effect of airfoil pitching motion on lift coefficient^[14]

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图 4 带后掠角翼型的表面流动^[19]

Figure 4. Surface flow of airfoil with sweepback angle^[19]

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图 5 钝后缘翼型在反流中的流动显示结果^[28]

Figure 5. Flow visualization of blunt tail airfoil in reverse flow^[28]

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图 6 X2TD和XH–59A桨叶根部翼型对比^[25]

Figure 6. Comparison of propeller shank between X2TD and XH–59A^[25]

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图 7 座头鲸鳍肢^[32]

Figure 7. Flipper of a humpback whale^[32]

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图 8 正弦前缘产生的流动结构示意图^[35]

Figure 8. Schematic of flow structures produced by sinusoidal leading edge^[35]

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图 9 涡流发生器对升力系数的影响^[42]

Figure 9. Impact of VGs on lift coefficient^[42]

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图 10 2种规格的片状涡流发生器阵列^[44]

Figure 10. Two arrays of VGs^[44]

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图 11 带扰流板的翼型^[46]

Figure 11. Airfoil with spoiler^[46]

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图 12 襟翼处狭缝吹气示意图^[59]

Figure 12. Schematic of flap blowing slot^[59]

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图 13 沿展向排列的吹气孔阵列^[61]

Figure 13. Array of blowing holes along the spanwise direction^[61]

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图 14 协同射流结构简图^[67]

Figure 14. Schematic of CFJ^[67]

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图 15 布置于翼梢附近的协同射流控制系统^[71]

Figure 15. CFJ near the wing tip^[71]

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图 16 交流等离子体激励器结构示意图^[77]

Figure 16. Schematic of AC–DBD^[77]

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图 17 AC–DBD和NS–DBD示意图^[84]

Figure 17. AC–DBD and NS–DBD^[84]

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图 18 合成射流激励器示意图^[89]

Figure 18. Schematic of synthetic jet^[89]

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图 19 合成射流作用下的翼型表面丝线流动显示结果^[103]

Figure 19. Surface flow visualization of airfoil under the control of synthetic jet^[103]

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图 20 合成双射流激励器结构示意及PIV试验结果^[104]

Figure 20. Schematic of dual synthetic jet and its related PIV result^[104]

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图 21 固定偏转角度的后缘小翼^[107]

Figure 21. Trailing winglet with fixed defection angle^[107]

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图 22 后缘小翼对俯仰力矩系数的影响（红色实线：带控制）^[107]

Figure 22. Pitching moment change by trailing winglet (red solid line)^[107]

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图 23 20°后掠角翼型表面流线^[111]

Figure 23. Surface flow of airfoil with 20° sweepback angle^[111]

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图 24 带后缘小翼的模型^[117]

Figure 24. Airfoil with active trailing winglet^[117]

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图 25 翼型和小翼偏转角控制方式^[118]

Figure 25. Controlling strategy of airfoil and trailing winglet^[118]

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图 26 鱼骨形机翼^[128]

Figure 26. Fishbone airfoil^[128]

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图 27 鱼骨形后缘小翼^[130]

Figure 27. Fishbone trailing winglet^[130]

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表 1 旋翼系统流动控制方法对比

Table 1. Comparison of flow methods for rotor system

流动控制方法	控制原理	主要优点	主要缺点	实现难易度	应用于旋翼的案例
优化翼型几何构型	改变翼型升阻特性	结构简单，稳定可靠	非定常状态控制效率低	容易	H160直升机^[24]，验证机X2TD^[25]
添加表面机械结构	改变边界层能量分布和外部流场结构	结构简单，稳定可靠	非定常状态控制效率低，产生“废阻”多	主动式控制较难	EC−145^[26]
吹气控制	注入高能射流	控制效率高	系统结构复杂	供气系统难实现	仅有专利
等离子体控制	电场诱导射流	结构简单，体积小	极端环境适应力弱，能效比低	电源和控制系统较难实现	仅有专利
合成射流控制	振动腔赋能射流	无需气源	极端环境适应力弱，高速条件下控制效率低	复杂流场下较难实现	仅有专利
后缘小翼控制	改变外部流场结构	控制效率高	控制机构和策略待优化	主动式控制较难	MD900风洞模型^[27]

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