尾缘控制措施对开式空腔噪声抑制效果研究

doi:10.3969/j.issn.1000-1093.2018.01.019

摘要/Abstract

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.

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

Abstract: 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 sound pressure level (SPL) inside the cavity reaches to 23 dB. Key

Key words: opencavity, aerodynamicnoise, flowcontrol, numericalsimulation, improveddelayeddetachededdysimulation

中图分类号:

V211.3

张群峰，闫盼盼，黎军. 尾缘控制措施对开式空腔噪声抑制效果研究[J]. 兵工学报, 2018, 39(1): 170-181.

ZHANG Qun-feng, YAN Pan-pan, LI Jun. Research on Suppression Effect of Rear Edge Control Method on Aerodynamic Noise in Open Cavity[J]. Acta Armamentarii, 2018, 39(1): 170-181.

参考文献

［1］ Krishnamurty K. Acoustic radiation from two dimensional rectangular cutouts in aerodynamic surfaces, TN 3487 [R]. Pasadena, CA, US: California Institute of Technology, 1955.
[2］ Charwat A F. An investigation of separated flows-part I: the pressure field[J]. Journal of the Aerospace Sciences, 1961, 28(5): 457-470.
[3］ Rossiter J E. Wind tunnel experiments on the flow over rectangular cavities at subsonic and transonic speeds[R]. Farnborough: Royal Aircraft Establishment, 1964.
[4］ Heller H H, Holmes D G, Covert E E. Flow induced pressure oscillations in shallow cavities[J]. Journal of Sound and Vibration, 1971, 18(4):545-546.
[5］ Covert E, Bilanin A J. Estimation of possible excitation frequencies for shallow rectangular cavities[J]. AIAA Journal, 1973, 11(3): 347-351.
[6］黎军, 李天, 张群峰. 开式流动腔体的流动机理与控制[J]. 实验流体力学, 2008, 22(1): 80-83.
LI Jun, LI Tian, ZHANG Qun-feng. The mechanism and control of open cavity flow[J]. Journal of Experiments in Fluid Mechanics, 2008, 22(1):80-83. (in Chinese)
[7］黎军, 张群峰, 曾宏刚, 等. 腔体闭式流动控制的实验和数值模拟[J]. 北京航空航天大学学报, 2008, 34(1): 96-99.
LI Jun, ZHANG Qun-feng, ZENG Hong-gang. Experiment and numerical investigation of controls for closed cavity flow[J]. Journal of Beijing University of Aeronautics and Astronautics, 2008, 34(1): 96-99. (in Chinese)
[8］ Givogue G, Vakili A, Fowler W.An experimental investigation of 2-D cylinders affecting supersonic cavity flow[C]∥29th AIAA Applied Aerodynamics Conference. Honolulu, HI, US: AIAA, 2011.
[9］ Thieman C C, Vakili A. An experimental investigation of supersonic cavity flow control with vertical cylinders[C]∥43rd AIAA Fluid Dynamics Conference. San Diego, CA, US: AIAA, 2013.

[10］刘瑜, 童明波. 基于DDES算法的有扰流片腔体气动噪声分析[J]. 空气动力学学报, 2015, 33(5): 643-648.
LIU Yu, TONG Ming-bo. DDES of aero-acoustic over an open cavity with and without a spoiler[J]. Acta Aerodynamica Sinica, 2015, 33(5): 643-648. (in Chinese)
[11］余培汛, 白俊强, 郭博智. 剪切层形态对开式空腔气动噪声的抑制[J]. 振动与冲击, 2015, 34(1): 156-164.
YU Pei-xun, BAI Jun-qiang, GUO Bo-zhi. Suppression of aerodynamic noise by altering the form of shear layer in open cavity[J]. Journal of Vibration and Shock, 2015, 34(1): 156-164. (in Chinese)
[12］吴继飞, 徐来武, 范召林, 等. 开式空腔气动声学特性及其流动控制方法[J]. 航空学报, 2015, 36(7): 2155-2165.
WU Ji-fei, XU Lai-wu, FAN Zhao-lin, et al. Aero acoustic characteristics and flow control method of open cavity flow[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(7): 2155- 2165. (in Chinese)
[13］陶洋, 吴继飞, 徐来武, 等. 基于前缘边界层扰动的空腔压力脉动抑制研究[J]. 实验流体力学, 2016, 30(3):66-70.
TAO Yang, WU Ji-fei, XU Lai-wu, et al. Control of cavity flow pressure oscillation through leading edge boundary layer perturbation[J］. Journal of Experiments in Fluid Mechanics, 2016, 30(3): 66-70. (in Chinese)
[14］ Williams D, Cornelius D, Rowley C.Closed-loop control of linear supersonic cavity tones[C]∥45th AIAA Fluid Dynamics Conference. Miami, FL, US: AIAA, 2007.
[15］杨党国, 吴继飞, 罗新福. 零质量射流对开式空腔气动噪声抑制效果分析[J]. 航空学报, 2011, 32(6): 1007-1014.
YANG Dang-guo, WU Ji-fei, LUO Xin-fu. Investigation on suppression effect of zero-net-mass-flux jet on aerodynamic noise inside open cavity[J］.Acta Aeronautica et Astronautica Sinica, 2011, 32(6): 1007-1014. (in Chinese)
[16］余培汛, 白俊强, 郭博智. 射流对空腔噪声抑制效果研究[J]. 计算力学学报, 2014, 31(5): 663-669.
YU Pei-xun, BAI Jun-qiang, GUO Bo-zhi. Suppression effect of jet flow on aerodynamic noise of cavity[J］.Chinese Journal of Computational Mechanics, 2014, 31(5): 663-669. (in Chinese)
[17］ Zhang Y, Arora N, Sun Y, et al. Suppression of cavity oscillations via three-dimensional steady blowing[C]∥45th AIAA Fluid Dynamics Conference. Dallas, TX, US: AIAA, 2015.
[18］王一丁, 郭亮, 童明波, 等. 高速飞行器空腔脉动压力主动控制与非线性数值模拟[J]. 航空学报, 2015, 36(1): 213-222.
WANG Yi-ding, GUO Liang, TONG Ming-bo, et al. Active control and nonlinear numerical simulation for oscillating pressure of high-speed aircraft cavity[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(1): 213-222. (in Chinese)
[19］宁方立, 史红兵, 丘廉芳. 前缘高频振动对亚声速开式空腔内强噪声影响的数值研究[J]. 航空学报, 2015, 36(12): 3843-3852.
NING Fang-li, SHI Hong-bing, QIU Lian-fang. Numerical research of high frequency vibration effect on subsonic open cavity macro-noise[J］.Acta Aeronautica et Astronautica Sinica, 2015, 36(12): 3843-3852. (in Chinese)
[20］ Blazek J. Computational fluid dynamics principles and applications[M]. Oxford, UK: Elsevier, 2005.
[21］ Venkatakrishnan V.On the accuracy of limiters and convergence to steady state solutions[C]∥31st Aerospace Sciences Meeting. Reno, NV, US: AIAA, 1994.
[22］ Shur M L, Spalart P R, Strelets M K. A hybrid RANS-LES approach with delayed-DES and wall-modeled LES capabilities[J]. International Heat and Fluid Flow, 2008, 29(6): 1638-1649.
[23］ Menter F R. Two-equation eddy-viscosity turbulence modeling for engineering application[J]. AIAA Journal, 1994, 32(8): 1598-1605.
[24］ Spalart P R, Jou W H, Strelets M, et al. Comments on the feasibility of LES for wings, and on a hybrid RANS/LES approach[C]∥Proceedings of the 1st AFOSR International Conference on DNS/LES. Ruston, LA, US:Greyden Press, 1997:4-8.
[25］ Spalart P R, Deck S, Shur M L, et al. A new version of detached-eddy simulation, resistant to ambiguous grid densities[J]. Theoretical and Computational Fluid Dynamics, 2006, 20(3): 181-195.
[26］张群峰, 闫盼盼, 黎军. 内埋式弹舱与弹体相互影响的精细模拟[J]. 兵工学报, 2016, 37(12):2366-2376.
ZHANG Qun-feng, YAN Pan-pan, LI Jun. Elaborate simulation of interaction effect between internal weapon bay and missile[J]. Acta Armamentarii, 2016, 37(12): 2366-2376. (in Chinese)
[27］ Quirk J. A contribution to the great Riemann solver debate[J]. International Journal for Numerical Methods in Fluids, 1994, 18(2): 555-574.
[28］ Aradag S, Knight D. Simulation of supersonic flow over a cavity[C]∥43rd AIAA Aerospace Sciences Meeting and Exhibit. Reno, NV, US: AIAA, 2005.
[29］ Henshaw M J C. M219 cavity case: verification and validation data for computational unsteady aerodynamics, RTO-TR-26 [R]. London, UK: QinetiQ, 2002.
[30］熊红亮, 袁格. 可压缩自由剪切层纹影试验研究[J]. 流体力学实验与测量, 2003, 17(2):74-77.
XIONG Hong-liang, YUAN Ge. Flow visualization about a compressible shear flow[J]. Experiments and Measurement in Fluid Mechanics, 2003, 17(2):74-77. (in Chinese)

第39卷
第1期2018 年1月兵工学报ACTA
ARMAMENTARIIVol.39No.1Jan.2018

[1]	严泽臣，岳松林，邱艳宇，王建平，赵跃堂，施杰，李旭. 水下爆炸冲击波反射压力计算方法的改进[J]. 兵工学报, 2024, 45(4): 1196-1207.
[2]	李婧, 孙晓霞, 马兴龙, 朱文祥. 开孔泡沫金属传热和流动特性[J]. 兵工学报, 2024, 45(1): 122-130.
[3]	康耕新, 颜海春, 张亚栋, 刘明君, 郝礼楷. 接触爆炸下混凝土墩破坏效应试验与数值模拟[J]. 兵工学报, 2024, 45(1): 144-155.
[4]	雷娟棉, 高毅, 勇政. 旋转导弹横向喷流干扰特性数值模拟[J]. 兵工学报, 2024, 45(1): 105-121.
[5]	王新宇, 姜春兰, 王在成, 方远德. 烤燃条件下JEO聚能装药战斗部泄压结构研究[J]. 兵工学报, 2024, 45(1): 1-14.
[6]	雷特, 武郁文, 徐高, 邱彦铭, 康朝辉, 翁春生. 基于大涡模拟方法的三维旋转爆轰流场结构研究[J]. 兵工学报, 2024, 45(1): 85-96.
[7]	周广盼, 王荣, 王明洋, 丁建国, 张国凯. 涂覆聚脲混凝土自锚式悬索桥主梁抗爆性能试验与数值模拟[J]. 兵工学报, 2023, 44(S1): 9-25.
[8]	寇永锋, 杨坤, 张斌, 肖迤文, 鲁建英, 陈朗. 基于烤燃实验和数值模拟的战斗部装药热安全性[J]. 兵工学报, 2023, 44(S1): 41-49.
[9]	余双洋, 彭永. 4340钢弹侵彻45号钢靶的温升数值模拟[J]. 兵工学报, 2023, 44(S1): 144-151.
[10]	余雯君, 陈胜云, 邓树新, 于冰冰, 晋冬艳. 爆炸冲击波在变向通道中传播规律数值模拟[J]. 兵工学报, 2023, 44(S1): 180-188.
[11]	杜永刚, 王雪松, 万志华. 助飞运载器螺旋传动失效的机理研究[J]. 兵工学报, 2023, 44(7): 2033-2040.
[12]	高铁锁, 江涛, 傅杨奥骁, 丁明松, 刘庆宗, 董维中, 许勇, 李鹏. 不同尺度飞行器周围等离子体分布及电磁波传输效应[J]. 兵工学报, 2023, 44(6): 1809-1819.
[13]	唐奎, 王金相, 刘亮涛, 杨明. 长杆弹二次侵彻机理及影响因素研究[J]. 兵工学报, 2023, 44(12): 3707-3718.
[14]	成乐乐, 黄风雷, 武海军, 田思晨, 陈文戈. 水下爆炸作用下多舱室结构的动力响应及损伤特性[J]. 兵工学报, 2023, 44(12): 3562-3579.
[15]	潘腾, 卞晓兵, 袁名正, 王亮亮, 黄元, 黄广炎, 张宏. 爆炸冲击波作用下聚氨酯-半球夹芯结构的动态响应[J]. 兵工学报, 2023, 44(12): 3580-3589.