直升机前飞状态旋翼结冰风洞试验研究

黄明其; 王亮权; 袁红刚; 彭先敏; 章贵川

doi:10.13700/j.bh.1001-5965.2020.0703

直升机前飞状态旋翼结冰风洞试验研究

doi: 10.13700/j.bh.1001-5965.2020.0703

中国空气动力研究与发展中心旋翼空气动力学重点实验室，绵阳 621000

基金项目:

国家自然科学基金 11902335

中国空气动力研究与发展中心基础和前沿技术研究基金 PJD20180146

详细信息

通讯作者:
王亮权, E-mail: wangliangquan@cardc.cn

中图分类号: V211.52
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出版历程
- 收稿日期: 2020-12-21
- 录用日期: 2021-02-20
- 网络出版日期: 2022-06-20
- 整期出版日期: 2022-06-20

Icing wind tunnel investigation of helicopter rotor model in forward flight state

Key Laboratory of Rotor Aerodynamics, China Aerodynamics Research and Development Center, Mianyang 621000, China

Funds:

National Natural Science Foundation of China 11902335

CARDC Fundamental and Frontier Technology Research Fund PJD20180146

More Information

Corresponding author: WANG Liangquan, E-mail: wangliangquan@cardc.cn

摘要

摘要:
为研究直升机旋翼在不同前飞状态的结冰情况，研制了直升机旋翼模型结冰试验台，在中国空气动力研究与发展中心结冰风洞4.8 m×3.2 m试验段中进行了旋翼结冰风洞试验。以某型直升机2 m直径旋翼缩比模型为试验对象，分析了旋翼转速、初始拉力系数对旋翼结冰的影响。结冰试验过程中保持旋翼操纵恒定，利用天平测量了旋翼拉力和扭矩性能的动态变化，并采用二维冰形切割及三维冰形扫描的方式分别测量了桨叶展向典型剖面的翼型及桨叶的整体结冰形态。试验得到了旋翼结冰关键数据，分析结果表明：旋翼桨叶结冰主要集中在桨叶前缘和下表面，结冰会在降低旋翼升力的同时增大旋翼扭矩和功率；小拉杆杆端轴承的积冰可能造成卡塞，变距拉杆上的积冰可能造成杆端轴承卡塞，从而使旋翼操纵失效。
- 直升机 /
- 旋翼 /
- 前飞状态 /
- 结冰风洞 /
- 气动性能
Abstract:
To investigate the effect of ice accretion on helicopter rotors in forward flight in different flight states, a helicopter rotor icing test system was developed. A rotor model icing test was conducted in the 4.8 m× 3.2 m test section of the China Aerodynamics Research and Development Center icing wind tunnel. The effect of the rotational speed and initial thrust on the performance of a 2 m-diamter rotor model was examined. During the icing test, the control angle of the rotor was maintained constant, and the dynamic variation of the rotor thrust and torque was measured by a balance. The ice shape of the airfoil at typical span stations and of the entire blade was measured by two-dimensional ice cutting and three-dimensional scanning system, respectively. Test results showed that ice accretion occurred primarily on the blade leading edge and lower surface, and that icing increased rotor torque and power while decreasing rotor thrust. The rod end bearing of the pitch link could be stuck by accreted ice, resulting in a loss of rotor control.
- helicopter /
- rotor /
- forward flight state /
- icing wind tunnel /
- aerodynamic performance

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图 1 安装在CARDC结冰风洞中的旋翼试验台

Figure 1. Rotor test rig installed in CARDC icing wind tunnel

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图 2 桨叶模型三视图

Figure 2. Three-view drawing of rotor blade model

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图 3 桨叶上的积冰情况

Figure 3. Ice accretion on rotor blade

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图 4 桨毂及变距机构上的积冰情况

Figure 4. Ice accretion on hub and pitch link

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图 5 基准试验状态(Case01)旋翼性能的变化

Figure 5. Time history of rotor performance for baseline case (Case01)

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图 6 基准试验状态(Case01)桨叶前缘的积冰特写

Figure 6. Close-up view of ice accretion on blade for baseline case (Case01)

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图 7 旋翼转速对旋翼性能的影响

Figure 7. Effect of rotational speed on rotor performance

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图 8 旋翼转速对翼型剖面冰形的影响

Figure 8. Effect of rotational speed on airfoil ice accretion

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图 9 Case02试验状态桨叶积冰照片

Figure 9. Picture of ice accretion on blade for test Case02

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图 10 Case03试验状态桨叶积冰照片

Figure 10. Picture of ice accretion on blade for test Case03

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图 11 初始拉力系数对旋翼性能的影响

Figure 11. Effect of initial thrust coefficient on rotor performance

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图 12 初始拉力系数对翼型剖面冰形的影响

Figure 12. Effect of initial thrust coefficient on airfoil ice accretion

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图 13 Case04试验状态的桨叶积冰扫描结果

Figure 13. Scan results of ice accreted on blade for test Case04

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图 14 Case05试验状态的桨叶积冰扫描结果

Figure 14. Scan results of ice accreted on blade for test Case05

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图 15 桨叶局部的积冰特写(Case04)

Figure 15. Picture of ice accretion on blade for test Case04

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表 1 旋翼结冰试验状态

Table 1. Icing conditions for rotor test

试验编号	来流速度/ (m·s^-1)	旋翼转速/ (r·min^-1)	拉力系数
Case01	37.7	1 800	0.008
Case02	37.7	1 080	0.008
Case03	37.7	1 440	0.008
Case04	37.7	1 800	0.006
Case05	37.7	1 800	0.010

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