尾缘控制措施对开式空腔噪声抑制效果研究  

Research on Suppression Effect of Rear Edge Control Method on Aerodynamic Noise in Open Cavity

作　　者：张群峰[1] 闫盼盼[1] 黎军[2] 

机构地区：[1]北京交通大学土木工程学院,北京100044 [2]中国航空工业集团有限公司沈阳飞机设计研究所,辽宁沈阳110035

出　　处：《兵工学报》2018年第1期170-181,共12页Acta Armamentarii

基　　金：国家自然科学基金项目(11172283)

摘　　要：利用基于Menter SST k-ω湍流模型的改进延迟分离涡模拟方法,对开式空腔气动声学特性进行了数值模拟研究,在腔体尾缘采用后壁开孔板加耗能腔的方法进行流动控制。分别研究了在亚声速和超声速来流条件下,所选取的控制措施对气动噪声的抑制效果;利用数值纹影方法等流场分析技术对开式空腔气动噪声的控制机理进行了分析。研究结果表明:亚声速来流条件下,耗能腔尺寸的选择对噪声抑制效果存在较大影响,若耗能腔尺寸过小,不但无法有效抑制腔体内气动噪声反而会使噪声水平大幅升高,最高升幅达12 dB;耗能腔尺寸增加后,腔体内噪声得到抑制,噪声降低幅度随着耗能腔尺寸的增加而增大。超声速来流条件下,所选用的控制措施可以有效地抑制腔体内气动噪声水平,开式空腔内自持振荡循环被终止,各阶模态频率的纯音噪声消失,噪声最高降幅达到23 dB.Improved delayed detached eddy simulation method based on Menter SST k-ω model is used to analyze the aero-acoustic characteristics of open cavity.Flow control method of porous rear wall combined with dissipative cavity is used to suppress the noise.The effects of aerodynamic noise suppression under the conditions of subsonic and supersonic inflows are analyzed.The control mechanism of aerodynamic noise from open cavity is studied using a variety of flow field analysis techniques,such as numerical schlieren method.The results show that the suppression effect is sensitive to the dissipative cavity length under the condition of subsonic inflow.If the dissipative cavity is too short,the noise level in open cavity can not be effectively suppressed by the control method,instead of increasing the noise level to 12 dB.The suppression effect is improved when increasing the length of dissipative cavity,the noise reduction level increases with the increase in dissipative cavity length.Under the condition of supersonic inflow,the aerodynamic noise inside the cavity is effectively suppressed by the control method,the self-sustained oscillation is terminated,the tone noise in the cavity disappears,and the maximum reduction of the soundpressure level（SPL） inside the cavity reaches to 23 dB.

关 键 词：开式空腔 气动噪声 流动控制 数值模拟 改进延迟分离涡模拟 

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]