共轴刚性旋翼悬停状态桨叶表面压力测量试验与计算研究

江露生; 曹亚雄; 刘婷; 樊枫

doi:10.13700/j.bh.1001-5965.2020.0669

共轴刚性旋翼悬停状态桨叶表面压力测量试验与计算研究

doi: 10.13700/j.bh.1001-5965.2020.0669

中国直升机设计研究所直升机旋翼动力学国家级重点实验室, 景德镇 333001

详细信息

通讯作者:
江露生, E-mail: jiangls@avic.com

中图分类号: V211.52
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出版历程
- 收稿日期: 2020-11-30
- 录用日期: 2021-01-08
- 网络出版日期: 2021-12-20

Experimental and computational study on blade surface pressure measurement of coaxial rigid rotor in hovering state

Science and Technology on Rotorcraft Aeromechanics Laboratory, China Helicopter Research and Development Institute, Jingdezhen 333001, China

More Information

Corresponding author: JIANG Lusheng, E-mail: jiangls@avic.com

摘要

摘要:
针对共轴刚性模型旋翼悬停状态，开展了桨叶表面压力测量试验与数值模拟研究。试验采用微型压力传感器进行桨叶表面压力测量，不仅获得了桨叶表面压力的试验数据，同时为CFD计算方法计算桨叶表面压力提供了验证数据。计算与试验结果对比吻合度良好，验证了CFD计算方法的有效性。研究获得了共轴刚性旋翼上下旋翼桨叶表面的流动情况和压力特性，结果表明：对于上下各4片桨叶的共轴刚性旋翼，桨叶表面压力随着桨叶旋转呈周期性变化，旋转一周出现8个小周期；在上下旋翼扭矩配平的悬停状态，下旋翼桨叶大部分区域受下洗流影响，下旋翼剖面拉力低于上旋翼；在桨尖区域，下旋翼的桨距角大于上旋翼，受各自上洗流的影响，下旋翼剖面拉力高于上旋翼。
- 共轴刚性旋翼 /
- 桨叶表面压力 /
- 压力测量试验 /
- 数值模拟 /
- 悬停状态
Abstract:
For the coaxial rigid model rotor in hovering state, the experimental and numerical simulation research on blade surface pressure measurement were carried out. The micro pressure sensor was used to measure the blade surface pressure, which not only obtains the experimental data of blade surface pressure, but also provides verification data for CFD method to calculate the blade surface pressure. The calculation results are in good agreement with the experimental results, which verifies the effectiveness of CFD method. The flow and pressure characteristics of the upper and lower rotor blade surface of the coaxial rigid rotor were obtained. The results show that, for coaxial rigid rotor with 4 upper blades and 4 lower blades, the blade surface pressure changes periodically with the rotation of the blade, and there are eight small cycles in one rotation cycle. In the hovering state of the upper and lower torque balancing, most of the area of the lower rotor blade is affected by the downwash flow, and the profile pull of the lower rotor is lower than that of the upper rotor; total pitch angle of the lower rotor in the tip region is larger than that of the upper rotor, and affected by respective upwash flow, the profile pull of the lower rotor is higher than that of the upper rotor.
- coaxial rigid rotor /
- blade surface pressure /
- pressure measurement experiment /
- numerical simulation /
- hovering state

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图 1 试验台及试验模型

Figure 1. Experimental station and experimental model

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图 2 无线遥测装置

Figure 2. Wireless telemetry device

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图 3 微型压力传感器

Figure 3. Micro pressure sensor

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图 4 剖面位置示意图

Figure 4. Schematic diagram of profile location

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图 5 共轴双旋翼嵌套网格

Figure 5. Coaxial dual-rotor overset grids

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图 6 桨叶表面压力系数计算与试验对比曲线(C_w=0.016 3)

Figure 6. Comparison of blade surface pressure coefficient between calculation and experiment (C_w=0.016 3)

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图 7 桨叶0.5R剖面压力系数计算与试验对比曲线(C_w=0.010 2)

Figure 7. Comparison of pressure coefficient of 0.5R blade profile between calculation and experiment (C_w=0.010 2)

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图 8 桨叶0.8R剖面压力系数计算与试验对比曲线(C_w=0.010 2)

Figure 8. Comparison of pressure coefficient of 0.8R blade profile between calculation and experiment (C_w=0.010 2)

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图 9 桨叶0.8R剖面测压点压力系数随方位角变化曲线(试验值)

Figure 9. Pressure coefficient variation with azimuth angle at pressure measuring point of 0.8R blade profile(experiment value)

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图 10 桨叶0.5R剖面测压点压力系数随方位角变化曲线(试验值)

Figure 10. Pressure coefficient variation with azimuth angle at pressure measuring point of 0.5R blade profile(experiment value)

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图 11 配平状态桨盘拉力分布

Figure 11. Distribution of disc traction in trimmed state

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图 12 上下旋翼轴向诱导速度云图(180°方位角)

Figure 12. Axial induced velocity contour of upper and lower rotor (180° azimuth angle)

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图 13 上下旋翼剖面压力云图(180°方位角)

Figure 13. Profile pressure contour of upper and lower rotor (180° azimuth angle)

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图 14 不同剖面位置压力系数分布(180°方位角)

Figure 14. Pressure coefficient distribution at different profile positions (180° azimuth angle)

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图 15 不同弦向位置点压力系数随方位角变化曲线(C_w=0.016 3)

Figure 15. Pressure coefficient variation with azimuth angle at different chordwise positions (C_w=0.016 3)

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图 16 同总距角状态桨盘拉力分布

Figure 16. Distribution of disc traction at the same total pitch angle

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图 17 同总距角状态拉力系数随方位角变化曲线

Figure 17. Traction coefficient variation with azimuth angle at the same total pitch angle

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图 18 同总距角状态不同剖面位置压力系数分布(180°方位角)

Figure 18. Pressure coefficient distribution at different profile positions at the same total pitch angle (180° azimuth angle)

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图 19 剖面点压力系数随方位角变化曲线

Figure 19. Pressure coefficient variation with azimuth angle at profile measuring point

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表 1 旋翼参数

Table 1. Rotor parameters

参数	数值
桨毂半径/mm	272
桨叶片数	4+4
旋翼旋转方向	上旋翼：逆时针; 下旋翼：顺时针
旋翼半径R/m	2
旋翼转速N/(r·min^-1)	778
旋翼间距	0.15R
翼型	OA3/4系列

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