Aerodynamic Noise Investigation of Metro Vehicle Auxiliary Converter
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摘要:为了解决地铁车辆辅助变流器噪声超标1.5 dB（A）的问题，基于数值模拟和噪声测试相结合的方法，对辅助变流器的气动噪声特性进行了分析. 首先通过大涡模拟计算辅助变流器的气动噪声源，然后基于声类比法计算气动噪声源在流道和外部空间的声传播，最后分析风机与流道的涡流和噪声分布云图，对比各测点声压级频谱仿真和试验结果的变化趋势. 研究结果表明：在距离出风口0.4 m处仿真和试验的峰值频率均为290 Hz，量值仅相差5%，说明仿真方法正确可行；风机进口速度不均匀度过大、风机叶片涡流过多是导致风机噪声过大的原因；通过在风机进口增加方形整流网，改善了风机进口速度不均匀度，减少了风机叶片涡流，实现相同测点总声压级降低2.5 dB（A）.Abstract:To solve the problem of a 1.5 dB (A) noise excess in a metro vehicle auxiliary converter, the aerodynamic noise characteristics of an auxiliary converter are investigated by combining a numerical simulation with a noise test. First, the noise from aerodynamic sources in the auxiliary converter was calculated using a large eddy simulation. Then, the sound propagation of aerodynamic sources of noise through ducts and surrounding spaces was calculated, based on an acoustic analogy method. Finally, the vortex and noise distribution contours in the fan and duct area were analysed, and trends in the simulation and test results of the sound pressure level spectrum at the test points were compared. The results indicate that at a distance of 0.4 m from the outlet, the peak frequency is 290 Hz under both conditions, and there is a 5% difference in amplitude. This demonstrates that the simulation method is correct and feasible. The vortex and noise distribution contours in the fan and duct area indicate that the inhomogeneity of air velocity at the fan inlet, and the significant vortex in the vicinity of the blade, are major contributions to the primary noise source, which is around the fan. By adding a thin, square-shaped honeycomb in front of the fan inlet, the velocity is rendered more uniform, and the overall sound pressure level is reduced by approximately 2.5 dB (A) at the test point.
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图 1辅助变流器气动噪声计算流程
Figure 1.Calculation flowchart for aerodynamic noise in auxiliary converter
图 8不同测点声压级频谱仿真与试验对比
Figure 8.Comparison between numerical simulation and test for sound pressure level spectrum at different measuring points
图 9气动噪声源的应力张量分布云图
Figure 9.Stress tensor distribution nephogram of aerodynamic noise source
图 13有无整流网的声压级频谱对比
Figure 13.Comparison of sound pressure spectrum with and without honeycomb
表 1前20阶空腔模态频率
Table 1.20 lowest-order mode frequencies of cavity Hz
阶次 频率 阶次 频率 1 70.14 11 283.79 2 82.36 12 300.61 3 106.44 13 311.58 4 191.87 14 312.38 5 210.89 15 323.05 6 219.42 16 339.41 7 226.37 17 351.97 8 227.91 18 360.01 9 247.14 19 364.64 10 257.33 20 371.32 
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