Interference noise reduction research of multiple propellers based on frequency domain method
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摘要:
为了研究多螺旋桨相同步降噪的机理，提出一种多螺旋桨旋转噪声快速预测方法，结合片条理论和Hanson频域模型来预测单螺旋桨噪声，基于线性理论将模型拓展至考虑旋转方向的多螺旋桨情况。该方法单点预测时间仅需20 ms，噪声预测结果与文献试验数据最大误差为4.03 dB。对影响相同步降噪性能的参数进行分析，结果表明：飞行高度、马赫数、安装距离对降噪性能影响较小为1～5 dB，叶片数、转速对于降噪性能影响较大为8～10 dB；在多叶片数目和多螺旋桨飞机上其降噪效果更显著。
Abstract:A fast prediction method for rotational noise of multi-propellers was presented in order to study the mechanism of synchrophasing noise reduction of multi-propellers. Combined with the strip theory and the Hanson frequency domain model, this method was used to predict the noise of single propeller, and the model was extended to consider the direction of rotation in the case of multi-propellers based on linear theory. The proposed method had a single point prediction time of only 20 ms and an maximum error of 4.03 dB when compared with experiment data from literature. The parameters affecting its performance were investigated. The results indicated that the flight altitude, Mach number, and installation distance had a small impact on the noise reduction performance, ranging from 1 dB to 5 dB, while the number of blades and rotational speed had a larger impact, ranging from 8 dB to 10 dB. The noise reduction effect was more significant for multi-blade configurations and multi-rotor aircraft.
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图 12 不同相角组合下的声压级
Figure 12. Sound pressure level under different phase angle combinations
图 15 不同飞行条件下的最大降噪效果
Figure 15. Maximum noise reduction effect under different flight conditions
图 16 不同转速和叶片数目的最大降噪效果
Figure 16. Maximum noise reduction effect at different speeds and blade numbers
图 17 不同安装距离下的最大降噪效果
Figure 17. Maximum noise reduction effect at different installation distances
表 1 用于验证的试验案例参数
Table 1. Test case parameters for validation
案例 螺旋桨 马赫数 前进比 1 SR-2 0.6 3.25 2 F8475D 0.2 0.7 
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表 2 双螺旋噪声指向性试验参数
Table 2. Noise directivity test parameters of dual-propeller
参数 数值及说明 参数 数值及说明 桨叶型号 CF125 转速/（r/min） 5100 直径/m 0.317 d/m 0.4 叶片数 2 Sr/m 1.9
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