轴向间距对单级风扇纯音噪声的影响

束王坚; 陈聪聪; 杜林; 孙晓峰

doi:10.13224/j.cnki.jasp.20220692

轴向间距对单级风扇纯音噪声的影响

doi: 10.13224/j.cnki.jasp.20220692

束王坚^1,,
陈聪聪¹,
杜林^2,*, ,,
孙晓峰^{1, 2}

1.
北京航空航天大学能源与动力工程学院，北京 102206
2.
北京航空航天大学航空发动机研究院，北京 102206

基金项目: 国家自然科学基金（52022009）；航空发动机及燃气轮机基础科学中心（P2022-A-Ⅱ-003-001）

详细信息

作者简介:
束王坚（1995-），男，博士生，主要从事压气机转静干涉噪声数值模拟研究

通讯作者:
杜林（1982-），男，研究员，博士，主要从事航空发动机气动弹性、气动声学研究。E-mail：lindu@buaa.edu.cn

中图分类号: V231
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- 被引次数: 0
出版历程
- 收稿日期: 2022-09-15
- 网络出版日期: 2023-11-20

Effect of axial spacing on tonal noise of a single-stage fan

SHU Wangjian^1
,,
CHEN Congcong¹,
DU Lin^{2,*
, ,},
SUN Xiaofeng^{1, 2}

1.
School of Energy and Power Engineering，Beihang University，Beijing 102206，China
2.
Research Institute of Aero-Engine，Beihang University，Beijing 102206，China

摘要

摘要:
针对单级风扇纯音噪声的远场声辐射预测，介绍了一种混合计算方法。其中，非线性谐波（NLH）方法用于转静干涉载荷声源的计算，声类比方法用以获得自由场的辐射声场，机匣的散射作用通过边界积分方法（BIEM）加以考虑。该混合方法可以同时预测管道内的声传播和管道外的声辐射。采用NASA的Advanced Noise Control Fan（ANCF）项目中的单级风扇作为研究对象，研究了实验间距下转静交界面位置的影响，确定交界面位置取在转静间距0.5倍，此时和远场声辐射实验结果最为接近。随后研究转静轴向间距对纯音噪声的影响，随着间距的减小，静子表面非定常载荷幅值、远场噪声指向性声压级相应增加。在低频下噪声指向性形状保持一致，高频噪声的指向性形状和声压级变化明显。
- 转静干涉 /
- 交界面 /
- 轴向间距 /
- 非线性谐波（NLH）方法 /
- 边界积分方法（BIEM）
Abstract:
An integrated computational approach was introduced for prediction of single-stage fan tonal noise. The nonlinear harmonic (NLH) method was used for computation of acoustic sources, the incidence wave in the free field was based on acoustic analogy, and the scattering wave generated by boundaries was solved by boundary integral element method (BIEM). The sound propagation inside the duct and radiation outside the duct can be predicted simultaneously. Then, the present method was applied to tonal noise prediction of the Advanced Noise Control Fan (ANCF) developed by NASA Glenn Research Center. The effect of interface locations was investigated at first as the experimental settings. The results indicated that the interface location at 0.5 times the axial spacing was most suitable for the computation of rotor-stator interaction, which was closest to the experimental results of tonal noise. Then, the effect of axial spacing on tonal noise was calculated. With the decrease of axial spacing, harmonic loading on the stator vanes and sound radiation in the far field showed an increasing trend. The shape of noise directivity at the first blade passing frequency (BPF) was similar, and the noise directivity at the second BPF showed big difference in shape and amplitude.
- rotor-stator interaction /
- interface /
- axial spacing /
- nonlinear harmonic (NLH) method /
- boundary integral element method (BIEM)

HTML

图 1 BIEM模型

Figure 1. Sketch of BIEM configuration

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图 2 ANCF结构和计算域

Figure 2. Configuration and computational domain of ANCF

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图 3 远场声压观察点位置示意图

Figure 3. Observer locations in the far field

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图 4 交界面位置和轴向间距示意图

Figure 4. Axial spacing and interface location

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图 5 3种交界面位置下1阶谐波压力幅值分布

Figure 5. 1st harmonic pressure amplitude of 3 interface locations

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图 6 3种交界面位置下BPF噪声远场指向性

Figure 6. Noise directivity at BPF of 3 interface locations

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图 7 3种交界面位置下2阶谐波压力幅值分布

Figure 7. 2nd harmonic pressure amplitude of 3 interface locations

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图 8 0.95倍管道半径处2阶谐波压力幅值沿弦向分布

Figure 8. 2nd harmonic pressure amplitude at 0.95 span of duct radius along the chordwise direction

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图 9 3种交界面位置下2BPF噪声远场指向性

Figure 9. Noise directivity at 2BPF of 3 interface locations

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图 10 3种轴向间距下静子表面1阶谐波压力幅值分布

Figure 10. 1st harmonic pressure amplitude over the blade surface of 3 axial spacings

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图 11 3种轴向间距下BPF噪声远场指向性

Figure 11. Noise directivity at BPF of 3 axial spacings

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图 12 3种轴向间距下静子表面2阶谐波压力幅值分布

Figure 12. 2nd harmonic pressure amplitude over the blade surface of 3 axial spacings

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图 13 3种轴向间距下0.95倍半径处2阶谐波压力幅值

Figure 13. 2nd harmonic pressure amplitude at 0.95 span of 3 axial spacings

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图 14 3种轴向间距下2BPF噪声远场指向性

Figure 14. Noise directivity at 2BPF of 3 axial spacings

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表 1 ANCF叶片参数

Table 1. ANCF blade row characteristics

部件叶片数半径/m 弦长/m 叶尖间隙/mm

转子 16 0.609 0.133 0.75
静子 14 0.610 0.114

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表 2 边界条件

Table 2. Boundary conditions

参数数值

进口绝对总压/Pa 101325

绝对总温/K 288.15

湍流黏度/10⁻⁵ （m²/s） 2

出口静压/Pa 101300

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表 3 3种交界面位置气动性能

Table 3. Aerodynamic performance of 3 interface locations

参数数值

L/S 0.25 0.5 0.75

流量/（kg/s） 51.714 51.444 51.729

效率/% 74.9 73.3 76.9

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表 4 3种轴向间距下气动性能

Table 4. Aerodynamic performance of 3 axial spacings

参数 S/C

0.5 1 2

流量/（kg/s） 51.733 51.444 51.746

效率/% 74.9 73.3 74.9

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