双喷管超声速欠膨胀射流噪声特性研究

杨义; 苟金澜; 乐贵高; 邢成龙

doi:10.13224/j.cnki.jasp.20230276

双喷管超声速欠膨胀射流噪声特性研究

doi: 10.13224/j.cnki.jasp.20230276

杨义¹,
苟金澜²,
乐贵高^1,*, ,,
邢成龙³

1.
南京理工大学机械工程学院，南京 210094
2.
武汉第二船舶设计研究所，武汉 430064
3.
河南工业大学电气工程学院，郑州 450001

详细信息

作者简介:
杨义（1999-），男，硕士生，主要从事火箭发动机气动声学研究

通讯作者:
乐贵高（1964-），男，教授、博士生导师，博士，主要从事火箭燃气气体动力学研究。E-mail：leguigao@njust.edu.cn

中图分类号: V211.3
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出版历程
- 收稿日期: 2023-04-25
- 网络出版日期: 2024-10-16

Study on noise characteristics of supersonic under-expanded jets with twin-nozzle

1.
School of Mechanical Engineering，Nanjing University of Science and Technology，Nanjing 210094，China
2.
Wuhan Second Ship Design and Research Institute，Wuhan 430064，China
3.
School of Electrical Engineering，Henan University of Technology，Zhengzhou 450001，China

摘要

摘要:
为探索超声速欠膨胀射流在不同喷管间距条件下的流场特征和噪声传播机理，基于大涡模拟（LES）方法建立数值计算模型，对超声速欠膨胀射流的流场结构、射流近-远场的噪声声压分布规律进行计算。研究了喷管数量、喷管间距对声场的影响。利用Ffowcs Williams-Hawkings（FW-H）方程获取不同位置、不同角度的远场噪声特性；通过对近场信号接收点的时域压力脉动信号进行傅里叶变换获得近场噪声特性。研究发现：在两种喷管间距条件下，双射流呈现出对称和反对称的扑动模式（基频处），相较于单射流，不同的双射流扑动模式使得啸叫频率产生偏移。当喷管间距较小时，双射流近场压力脉动强度更大，近场噪声声压级幅值更大。射流远场声压级峰值频率随着观测角度的增大而升高，但在双射流平面内，两种工况下的噪声指向性变化趋势相同。
- 欠膨胀射流 /
- 气动噪声 /
- 大涡模拟 /
- 喷管间距 /
- Ffowcs Williams-Hawkings方程
Abstract:
In order to explore the flow field characteristics and noise propagation mechanism of an under-expanded supersonic jet under different nozzle spacing conditions, a numerical model was established based on the large eddy simulation (LES) method to calculate the flow field structure of under-expanded supersonic jet and the noise sound pressure distribution law of near-far field. The effects of the number of nozzles and the distance between nozzles on the sound field were studied. The far-field noise characteristics of different positions and angles were obtained based on the Ffowcs Williams-Hawkings (FW-H) equation; the near-field noise characteristics were obtained by performing Fourier transform on the time-domain pressure fluctuation signals of the near-field receivers. The results showed that under the condition of two kinds of nozzle spacing, the twin-jet presented symmetrical and anti-symmetrical flapping modes (at fundamental frequency); and compared with the single jet, the difference of the twin-jet flapping mode made the whistling frequency shift. When the distance between nozzles was small, the near-field pressure fluctuation intensity of twin-jet was greater, and the amplitude of near-field noise sound pressure level was larger. The peak frequency of the sound pressure level in the far field of the jet increased with the increase of the observation angle, but in the twin-jet plane, the change trend of noise directivity was the same under both working conditions.
- under-expanded jet /
- aerodynamic noise /
- large eddy simulation /
- nozzle spacing /
- Ffowcs Williams-Hawkings equation

HTML

图 1 计算域和边界条件示意图

Figure 1. Schematic diagram of computational domain and boundary conditions

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图 2 单射流网格划分示意图

Figure 2. Schematic diagram of grid division of single jet

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图 3 单射流流场结构对比图

Figure 3. Comparative diagram of flow field structure of single jet

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图 4 瞬时压力脉动云图

Figure 4. Instantaneous pressure fluctuation nephogram

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图 5 近场压力脉动谱

Figure 5. Near-field pressure fluctuation spectra

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图 6 噪声接收点位置示意图

Figure 6. Schematic diagram of position of noise receiving points

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图 7 双射流三维柱面网格图

Figure 7. Three-dimensional cylindrical grid for twin-jet

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图 8 双喷管近场网格划分

Figure 8. Grid topology near twin-nozzle exit

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图 9 雷诺平均密度等值线图

Figure 9. Reynolds averaged density contours

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图 10 瞬时压力等值面图

Figure 10. Instantaneous pressure iso-surface

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图 11 近场瞬时压力脉动图

Figure 11. Near-field instantaneous pressure fluctuation

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图 12 基频处的傅里叶相场

Figure 12. Fourier phase fields at fundamental component

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图 13 近场P₁和P₀点的声压脉动谱

Figure 13. Near-field pressure fluctuation spectra in points P₁ and P₀

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图 14 基频处的近场声压图（单位：dB）

Figure 14. Near-field sound pressure graph at fundamental component （unit：dB）

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图 15 双射流远场噪声接受点示意图

Figure 15. Schematic diagram of far-field noise receiving points of twin-jet

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图 16 远场噪声接受点的总声压级

Figure 16. Overall sound pressure level of far-field noise receiving points

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图 17 远场噪声接受点声压频谱图

Figure 17. Sound pressure spectrum of far-field noise receiving points

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表 1 计算-实验误差

Table 1. Calculation-experimental error

θ/（°）	计算值/dB	实验值/dB	误差/%
40	120.161	121.5	1.10
45	116.985	119	1.69
50	114.863	118	2.65
60	110.114	117.5	6.28
70	111.258	118	5.71
75	109.642	120	8.63
80	110.94	122	9.06
90	111.331	120	7.22
100	111.37	118	5.61

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