基于IDDES数值模拟的双发螺旋桨相位控制降噪研究

何慧娴; 王跃; 宋文萍; 韩忠华; 刘松; 曹德松

doi:10.13224/j.cnki.jasp.20240370

基于IDDES数值模拟的双发螺旋桨相位控制降噪研究

doi: 10.13224/j.cnki.jasp.20240370

何慧娴^{1, 2, 3,},
王跃^{1, 2, 3,*, ,},
宋文萍^{1, 2},
韩忠华^{1, 2},
刘松⁴,
曹德松⁴

1.
西北工业大学航空学院，西安 710072
2.
西北工业大学飞行器基础布局全国重点实验室，西安 710072
3.
中国空气动力研究与发展中心空天飞行空气动力科学与技术全国重点实验室，四川绵阳 621000
4.
中国航空工业集团有限公司惠阳航空螺旋桨有限责任公司，河北保定 071051

基金项目: 陕西省自然科学基础研究计划资助项目（2023-JC-ZD-01）；气动噪声控制重点实验室开放课题（2301ANCL20230202）

详细信息

作者简介:
何慧娴（2000-），女，硕士生，主要从事螺旋桨气动声学方面的研究。E-mail：zxhehuixian@mail.nwpu.edu.cn

通讯作者:
王跃（1986-），男，副教授，博士，主要从事计算气动声学方面的研究。E-mail：yuewang@nwpu.edu.cn

中图分类号: V211.3
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出版历程
- 收稿日期: 2024-06-06
- 网络出版日期: 2024-12-13

Study on noise reduction by phase control of twin propellers using IDDES numerical simulations

HE Huixian^{1, 2, 3
,},
WANG Yue^{1, 2, 3,*
, ,},
SONG Wenping^{1, 2},
HAN Zhonghua^{1, 2},
LIU Song⁴,
CAO Desong⁴

1.
School of Aeronautics，Northwestern Polytechnical University，Xi’an 710072，China
2.
National Key Laboratory of Aircraft Configuration Design，Northwestern Polytechnical University，Xi’an 710072，China
3.
State Key Laboratory of Aerodynamics，China Aerodynamics Research and Development Center，Mianyang Sichuan 621000，China
4.
Huiyang Aviation Propeller Company Limited，Aviation Industry Corporation of China，Limited，Baoding Hebei 071051，China

摘要

摘要:
螺旋桨相位控制技术是一种有效的涡桨飞机主动控制降噪方法。目前，针对该技术的研究主要依赖于理论分析和试验研究，这些方法在揭示流场细节和理解降噪机理方面存在一定的局限性。采用改进延迟分离涡模拟（IDDES）结合Ffowcs Williams-Hawkings（FW-H）方程的声类比方法，对某型涡桨飞机的双桨缩比模型开展了相位控制降噪研究，详细分析了不同相角差对双螺旋桨系统降噪性能的影响，并深入探讨了螺旋桨相位控制的流动机理。研究结果表明：本文采用的数值方法能够有效模拟双发螺旋桨的相位控制降噪效果。通过调整螺旋桨间相角差，在特定观测点实现了噪声水平的显著降低。以双桨桨盘平面的桨轴连线中点为例，当相角差设置为30°时，相较于0°相角差，该观测点的总声压级降低了15.37 dB。该点处压力和密度脉动幅值显著减小，显示出高压区与低压区干涉相消的典型相位控制降噪特征。桨盘平面的压力脉动和密度脉动分布呈现涡旋花瓣状的辐射特征。进一步分析表明：随着双桨间相角差的增加，双桨中心连线中点处的厚度噪声和载荷噪声分量先减少后增加，在相角差为30°时达到最小值。
- 相位控制降噪 /
- 双发螺旋桨 /
- 改进延迟分离涡模拟（IDDES）数值模拟 /
- Ffowcs Williams-Hawkings（FW-H）声类比 /
- 相角差 /
- 流动机理分析
Abstract:
Propeller phase control technology is an effective active noise control method for turboprop aircraft. Current research on this technology primarily relies on theoretical analysis and experimental studies, which have certain limitations in revealing flow field details and understanding noise reduction mechanisms. An improved delayed detached eddy simulation (IDDES) combined with the Ffowcs Williams-Hawkings (FW-H) acoustic analogy method was employed to conduct phase control noise reduction research on a scaled twin-propeller model of a specific turboprop aircraft. Detailed analysis of the impact of phase angle differences on the noise reduction performance of a twin-propeller system was conducted, offering an in-depth exploration of the flow mechanisms associated with propeller phase control. The results indicated that the numerical method used can effectively simulate the phase control noise reduction effects of twin engines. By adjusting the phase angle differences between the propellers, a significant reduction in noise levels was achieved at specific observation points. For instance, at the midpoint of the shaft line in the twin-propeller disk plane, when the phase angle difference was set to 30°, the overall sound pressure level at this observation point was reduced by 15.37 dB compared with 0° phase angle difference. The pressure and density fluctuation amplitudes at this point were significantly reduced, demonstrating the typical phase control noise reduction characteristic of interference cancellation between high and low-pressure areas. The distribution of pressure and density fluctuations on the disk plane exhibited a swirling petal-like radiation pattern. Further analysis showed that as the phase angle difference between the twin propellers increased, the thickness noise and loading noise components at the midpoint of the centerline between the propellers first decreased and then increased, reaching their minimum values at a phase angle difference of 30°.
- Noise reduction by phase control /
- twin propellers /
- improved delayed detached eddy simulation (IDDES) /
- Ffowcs Williams-Hawkings (FW-H) acoustic analogy /
- phase angle difference /
- flow mechanism analysis

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图 1 数值模拟流程

Figure 1. Flowchart of numerical simulation

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图 2 远场噪声旋转平面观测点设置

Figure 2. Points of noise observation in far field

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图 3 流场区域划分图

Figure 3. Diagram of flow field partitioning

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图 4 网格划分示意图

Figure 4. Diagram of mesh division

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图 5 噪声计算值与试验值对比图

Figure 5. Comparison of calculated noise values and experimental values

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图 6 网格划分示意图

Figure 6. Diagram of mesh division

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图 7 远场噪声观测点示意图

Figure 7. Schematic diagram of far-field noise observation points

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图 8 双桨缩比模型图

Figure 8. Scaled model diagram of twin propellers

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图 9 双桨相对位置分布

Figure 9. Relative position distribution of twin propellers

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图 10 总声压级随网格量变化曲线

Figure 10. Curve of overall sound pressure level variation with cell number

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图 11 轴向线阵噪声观测点示意图

Figure 11. Noise directivity of observation points in axial linear array

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图 12 不同相角差下的轴向线阵上各点噪声值对比图

Figure 12. Comparison of noise between different phase angle differences in axial array

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图 13 桨轴连线中点处的噪声变化曲线

Figure 13. Noise variation curve at the midpoint between the twin-propeller shafts

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图 14 相角差为0°和30°时的压力脉动绝对值云图及局部等值线放大图

Figure 14. Absolut pressure pulsation cloud map and local enlarged map at the phase angle differences are 0° and 30°

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图 15 相角差为0°和30°时的密度脉动云图

Figure 15. Density pulsation cloud map at the phase angle differences are 0° and 30°

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图 16 相角差为0°和30°时桨轴连线中点对应的压力脉动与声压频谱图

Figure 16. Pressure pulsation and sound pressure spectra corresponding to the midpoint of propellers at the phase angle differences are 0° and 30°

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图 17 圆形阵列噪声观测点示意图

Figure 17. Noise observation points of circular array

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图 18 对称平面观测点噪声指向性

Figure 18. Noise directivity of observation points in symmetry plane

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图 19 周向平面观测点噪声指向性

Figure 19. Noise directivity of observation points in circumferential plane

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图 20 旋转平面观测点噪声指向性

Figure 20. Noise directivity of observation points in rotation plane

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图 21 相角差为0°和30°时旋转平面观测点噪声指向性

Figure 21. Noise directivity of observation points in rotation plane when phase angle differences are 0° and 30°

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图 22 不同相角差下的双桨桨轴连线中点处噪声分解结果对比

Figure 22. Comparison of noise decomposition results at the midpoint of the double propeller shaft connection under different phase angle differences

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表 1 远场观测点总声压级计算值与试验值对比

Table 1. Comparison between calculated and experimental OASPL values of observation points

观测点序号	总声压级/dB			相对误差/%
观测点序号	计算值	试验值	误差	相对误差/%
1	73.943	74.221	−0.278	−0.37
2	73.487	73.360	0.128	0.17
3	73.181	72.483	0.698	0.96

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表 2 不同时刻桨轴连线中点处总声压级

Table 2. Comparison of OASPL at the midpoint of the twin-propeller shafts at different times

相角差/（°）	总声压级/dB
相角差/（°）	t_p=0.1515	t_p=0.1538	t_p=0.1561	t_p=0.1584	t_p=0.1607
0	130.432	130.431	130.433	130.445	130.445
10	129.123	129.122	129.125	129.136	129.136
20	124.439	124.437	124.439	124.431	124.430
30	113.688	113.682	113.683	113.688	113.687
40	124.441	124.448	124.441	124.443	124.443
50	129.123	129.120	129.121	129.122	129.123

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