基于SNGR方法研究增升装置缝翼噪声的抑制效果  

Aerodynamic noise suppression of slats by using a SNGR method

作　　者：余培汛[1,2] 潘凯[1] 白俊强[2] 韩啸[2] YU Peixun;PAN Kai;BAI Junqiang;HAN Xiao(Aircraft Strength Research Institute of China,Laboratory of Aeronautical Acoustics and Dynamics,Xi’an 710065,China;School of Aeronautics,Northwestern Polytechnic University,Xi’an 710072,China)

机构地区：[1]中国飞机强度研究所,航空声学与动强度航空科技重点实验室,西安710065 [2]西北工业大学,航空学院,西安710072

出　　处：《振动与冲击》2018年第4期110-115,169,共7页Journal of Vibration and Shock

摘　　要：耦合湍流速度生成模型与声传播方程,形成了一套具备模拟声源在非均匀流场中传播的CAA混合预测方法,即SNGR方法。针对SNGR方法的可靠性验证,选用了30P30N标模的缝翼噪声传播算例,对比分析缝翼后缘某监测点的声压频谱曲线及辐射噪声指向性云图,其计算结果与参考文献结果吻合度较好。在此基础上,设计了几种不同几何形状的缝翼构型,研究其对气动噪声的抑制效果。采用SNGR方法对比分析了各构型的声压分布云图、噪声指向性云图,并通过LES/FWH方法对噪声抑制效果进行了验证分析,结果表明:通过延长前缘缝翼长度可有效增强剪切层的稳定性,降低剪切层与缝翼背风区壁面碰撞的强度,从而达到抑制噪声的效果;SNGR方法能有效应用到二维增升装置的噪声预测及抑制问题中。Coupled with the turbulent velocity generation model and the sound propagation equation,a SNGR(Stochastic Noise Generation and Radiation)method which was able to simulate the noise source propagation in a non-uniform flow field was formed.In order to validate the SNGR method,the noise propagation of the 30P30N model’s slat was selected.Comparing the frequency spectrum of the monitor at the trailing edge of the slat and the contour of noise directivity,numerical results are well consistent with the results in literature.Several different geometrical configurations of slats were designed.Adopting the SNGR method,the acoustic pressure contour and noise directivity contour of each configuration were analyzed,and the noise depressing effects were validated by means of the LES/FWH method.The result shows:1.By extending the effective length of the leading edge of the slat,the stability of shear layer is strengthened and the intensity of the collision between shear layer and leeward region of slat is decreased.Because of these reasons,the noise of the slat is reduced.2.The SNGR method can be applied to noise prediction and suppression of two-dimensional high-lift configurations.

关 键 词：湍流速度生成模型 声传播方程 缝翼 气动噪声 剪切层 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程] V211.4