Experimental study on mode characteristics of screech tone by rectangular supersonic jet
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摘要:
针对圆形及宽高比分别为1、1.5、2、10的4种矩形收缩喷管的超声速射流激波啸叫噪声的周向模态特性开展了实验测量研究。所有喷口具有相同的出口面积，并在同一射流模拟装置中进行，射流为冷喷流。研究在喷口出口近场区域周向等角度布置12个传声器，采用短时互功率谱分析方法和短时滤波声能分析方法分别获得超声速欠膨胀射流激波啸叫相位及幅值的周向角分布情况。研究表明：宽高比为1的矩形超声速欠膨胀射流的模态特性与圆形射流基本一致，而宽高比大于1的矩形射流模态特性与圆形射流差异较大。低马赫数下，圆形和宽高比为1的矩形射流表现出稳定的轴对称模态，而宽高比大于1的矩形射流表现出不稳定的模态特征；较高马赫数下，圆形和宽高比为1的矩形射流表现出不稳定的螺旋或摆动模态，而宽高比大于1的矩形射流表现出稳定的沿短轴方向的摆动模态。
Abstract:The azimuthal mode characteristics of supersonic jet screech tone noise were studied for four converging rectangular jets of aspect ratios 1, 1.5, 2 and 10 and a round nozzle. All five nozzles had the same exit area and were tested in the same jet simulator facility on unheated conditions. Twelve microphones were arranged at equal azimuthal angles in the near-field of the nozzle outlet. The azimuthal angular distribution of the phase and amplitude of the screech tone of supersonic under expanded jet was obtained using the short-time cross power spectrum analysis method and the short-time filtered sound energy analysis method. It was found that the mode characteristics of rectangular supersonic under-expanded jet with aspect ratio of 1 were basically consistent with those of circular jet, while the mode characteristics of rectangular jet with aspect ratio greater than 1 were quite different from those of circular jet. At low Mach number, circular and rectangular jets with aspect ratio 1 showed stable axisymmetric modes, while rectangular jets with aspect ratio greater than 1 showed unstable mode characteristics. At higher Mach numbers, circular and rectangular jets with aspect ratio 1 exhibited unstable helical or oscillating modes, while rectangular jets with aspect ratio greater than 1 exhibited stable oscillating modes along the minor axis.
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Key words:
- supersonic jet /
- jet noise /
- rectangular jet /
- screech tone /
- mode characteristic
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图 2 实验研究用的矩形收缩段和喷口照片
Figure 2. Photograph of rectangular contraction and nozzles for experimental research
图 5 圆形射流周向相邻测点互功率谱密度典型结果
Figure 5. Typical results of cross-power spectral density at adjacent azimuthal measuring points of circular jet
图 6 圆形超声速欠膨胀射流啸叫声无量纲频率理论与实验结果的对比
Figure 6. Theory and experimental results of screech tone fre-quency of round jet
图 7 矩形射流啸叫率理论和实验结果
Figure 7. Theory and experimental results of screech tone frequency of rectangular jet
图 8 圆形射流周向不同位置相对相位结果（Ma=1.09）
Figure 8. Relative phase results of circular jet at different azimuthal position （Ma=1.09）
图 9 圆形射流周向不同位置相对相位结果（Ma=1.25）
Figure 9. Relative phase results of circular jet at different azimuthal position （Ma=1.25）
图 10 矩形射流周向不同位置相对相位结果（Ma=1.09）
Figure 10. Relative phase results of rectanglar jet at different azimuthal position （Ma=1.09）
图 11 矩形射流周向不同位置相对相位结果（Ma=1.25）
Figure 11. Relative phase results of rectanglar jet at different azimuthal position （Ma=1.25）
图 12 宽高比为1的矩形射流远场噪声频谱（Ma=1.23）
Figure 12. Far field noise spectrum of rectanglar jet with aspect ratio 1 （Ma=1.23）
图 13 宽高比为1的矩形射流周向不同位置相对相位结果（Ma=1.23）
Figure 13. Relative phase results at different azimuthal position of rectanglar jet with aspect ratio 1 （Ma=1.23）
图 14 圆形射流周向不同位置相对声压结果（Ma=1.09）
Figure 14. Normalized sound pressure results of circular jet at different azimuthal position （Ma=1.09）
图 15 圆形超声速射流周向不同位置相对声压结果（Ma=1.25）
Figure 15. Normalized sound pressure results of circular chocked jet at different azimuthal position（Ma=1.25）
图 16 矩形超声速射流周向不同位置某时刻相对声压结果（宽高比为1，Ma=1.09）
Figure 16. Normalized sound pressure results of rectangular chocked jet at different azimuthal position at some instant time （aspect ratio 1, Ma=1.09）
图 17 矩形超声速射流周向不同位置不同时刻相对声压结果（宽高比为1.5，Ma=1.09）
Figure 17. Normalized sound pressure results of rectangular chocked jet at different azimuthal position with different times （aspect ratio 1.5, Ma=1.09）
图 18 矩形超声速射流周向不同位置不同时刻相对声压结果（宽高比为1，Ma=1.25）
Figure 18. Normalized sound pressure results of rectangular chocked jet at different azimuthal position with different times（aspect ratio 1, Ma=1.25）
图 19 矩形超声速射流周向不同位置不同时刻相对声压结果（宽高比为1.5，Ma=1.25）
Figure 19. Normalized sound pressure results of rectangular chocked jet at different azimuthal position with different times （aspect ratio 1.5, Ma=1.25）
图 20 矩形超声速射流周向不同位置不同时刻相对声压结果（宽高比为2，Ma=1.25）
Figure 20. Normalized sound pressure results of rectangular chocked jet at different azimuthal position with different times（aspect ratio 2, Ma=1.25）
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