单喷管火箭燃气导流环境下的噪声分析
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摘要
火箭发射时的发动机喷流噪声是航天发射的主要外激励源,噪声大小也是结构和仪器设备设计与验证的技术指标之一。该文以单台火箭发动机喷流经过单侧导流槽气流诱发的噪声问题为对象,通过求解三维可压缩流动Navier-Stokes方程,建立某火箭发动机喷流噪声激励数值预测方法,其中流通量采用二阶Roe TVD差分格式,并采用中心差分离散SAS湍流模型的耗散项,通过计算声类比Ffowcs Williams-Hawkings(FW-H)方程得出喷流噪声激励,数值仿真结果与实测数据吻合良好,并分析了噪声传播延时及其地面分布规律。分析结果表明,发动机喷流噪声主要表现为宽频带噪声,随着噪声监测点和发动机喷口之间距离的增加,总声压级呈现出衰减趋势。
As a main source of external excitation,the noise level of jet flow of lift-off rockets is also one of the criterions for design and verification of structure and equipment. To establish a kind of numerical methodology for predicting acoustic level of a rocket engine,the jet noise of deflected flow for the single nozzle rocket is studied by solving the 3-D Navier-Stokes formulas of the compressible flow field in this paper,and the convective flux is analyzed by the 2 nd order Roe TVD difference method and the dissipation term of SAS turbulence model is computed by means of the central difference method. The acoustic excitation is acquired by the Ffowcs Williams-Hawkings(FW-H)theroy. Computational results are reasonablly in accordance with experimental data. The transmission delay characteristic and the circumferential distribution for noise level on the ground is also analyzed. The results show that the noise of jet flow of the rocket engine is mainly in a broad frequency band distribution,and the overall sound pressure levels are reduced as the distance from the receiver to the nozzle increases.
As a main source of external excitation,the noise level of jet flow of lift-off rockets is also one of the criterions for design and verification of structure and equipment. To establish a kind of numerical methodology for predicting acoustic level of a rocket engine,the jet noise of deflected flow for the single nozzle rocket is studied by solving the 3-D Navier-Stokes formulas of the compressible flow field in this paper,and the convective flux is analyzed by the 2 nd order Roe TVD difference method and the dissipation term of SAS turbulence model is computed by means of the central difference method. The acoustic excitation is acquired by the Ffowcs Williams-Hawkings(FW-H)theroy. Computational results are reasonablly in accordance with experimental data. The transmission delay characteristic and the circumferential distribution for noise level on the ground is also analyzed. The results show that the noise of jet flow of the rocket engine is mainly in a broad frequency band distribution,and the overall sound pressure levels are reduced as the distance from the receiver to the nozzle increases.
引文
[1] 李锋,刘小勇,鲍福廷.火箭发动机噪声测试及预估研究[J].电声技术,2009,33(9):53-57Li Feng,Liu Xiaoyong,Bao Futing.Research on noise measuring and prediction of rocket engine[J].Audio Engineering,2009,33(9):53-57.
[2] 张津泽,徐珊姝,王国辉,等.超声速喷流噪声研究进展[J].强度与环境,2016,43(5):57-64.Zhang Jinze,Xu Shanshu,Wang Guohui,et al.Research progress of supersonic jet noise[J].Structure & Environment Engineering,2016,43(5):57-64.
[3] NASA-HDBK-7005.Dynamic Environmental Criteria[S].NASA Technical Handbook,2001:42-46.
[4] 陈劲松,曾玲芳,胡小伟,等.单喷管液体火箭发射喷流噪声模拟试验研究[J].空气动力学学报,2015,33(6):818-822.Chen Jinsong,Zeng Lingfang,Hu Xiaowei,et al.Test on launch jet noise of liquid rocket with single nozzle[J].Acta Aerodynamica Sinica,2015,33(6):818-822.
[5] 任方,张正平,李海波,等.运载火箭起飞噪声环境缩比模型试验方法[J].宇航学报,2015,36(3):344-350.Ren Fang,Zhang Zhengping,Li Haibo,et al.The lift-off acoustics prediction methods with scale model acoustic test of launch vehicle[J].Journal of Astronautics,2015,36(3):344-350.
[6] Menter F R,Kuntz M,Bender R.A scale-adaptive simulation model for turbulent flow predictions[R].AIAA Paper,2003:2003-0767.
[7] Houston J,Counter D,Giacomoni C.SLS scale model acoustic test lift-off results and comparisons[R].AIAA Paper,2015:2015-1607.
[8] 朱莹,马琳,董龙雷.火箭发动机喷流噪声数值模拟及声振分析[J].计算机辅助工程,2015,24(4):48-51.Zhu Ying,Ma Lin,Dong Longlei.Jet flow noise numerical simulation and acoustic-vibration analysis of rocket engine[J].Computer Aided Engineering,2015,24(4):48-51.
[9] 李军.单兵火箭燃气射流冲击噪声场的形成与发展[J].南京理工大学学报,2006,30(6):679-683.Li Jun.Forming and developing of impact jet noise flow field of individual rocket[J].Journal of Nanjing University of Science and Technology,2006,30(6):679-683.
[10] 樊孝峰,王江峰,赵法明.Roe格式在多组元燃烧流场数值模拟中的应用[J].南京航空航天大学学报,2016,48(3):347-351.Fan Xiaofeng,Wang Jiangfeng,Zhao Faming.Numerical simulation of multi-component reacting flow using Roe scheme[J].Journal of Nanjing University of Aeronautics & Astronautics,2016,48(3):347-351.
[11] Egorov Y,Menter F.Development and application of SST-SAS turbulence model in the DESIDER project[C]//Advances in Hybrid RANS-LES Modelling.Heidelberg,Berlin,Germany:Springer,2008:261-270.
[12] Younsi M,Djerrada A,Belamri T,et al.Application of the SAS turbulence model to predict the unsteady flow field behaviour in a forward centrifugal fan[J].International Journal of Computational Fluid Dynamics,2008,22(9):639-648.
[13] 胡声超,鲍福廷,赵瑜.多喷管射流气动声学特性的数值研究[J].推进技术,2012,33(3):430-435.Hu Shengchao,Bao Futing,Zhao Yu.Numerical simulation for multi-jet aeroacoustics[J].Journal of Propulsion Technology,2012,33(3):430-435.
[2] 张津泽,徐珊姝,王国辉,等.超声速喷流噪声研究进展[J].强度与环境,2016,43(5):57-64.Zhang Jinze,Xu Shanshu,Wang Guohui,et al.Research progress of supersonic jet noise[J].Structure & Environment Engineering,2016,43(5):57-64.
[3] NASA-HDBK-7005.Dynamic Environmental Criteria[S].NASA Technical Handbook,2001:42-46.
[4] 陈劲松,曾玲芳,胡小伟,等.单喷管液体火箭发射喷流噪声模拟试验研究[J].空气动力学学报,2015,33(6):818-822.Chen Jinsong,Zeng Lingfang,Hu Xiaowei,et al.Test on launch jet noise of liquid rocket with single nozzle[J].Acta Aerodynamica Sinica,2015,33(6):818-822.
[5] 任方,张正平,李海波,等.运载火箭起飞噪声环境缩比模型试验方法[J].宇航学报,2015,36(3):344-350.Ren Fang,Zhang Zhengping,Li Haibo,et al.The lift-off acoustics prediction methods with scale model acoustic test of launch vehicle[J].Journal of Astronautics,2015,36(3):344-350.
[6] Menter F R,Kuntz M,Bender R.A scale-adaptive simulation model for turbulent flow predictions[R].AIAA Paper,2003:2003-0767.
[7] Houston J,Counter D,Giacomoni C.SLS scale model acoustic test lift-off results and comparisons[R].AIAA Paper,2015:2015-1607.
[8] 朱莹,马琳,董龙雷.火箭发动机喷流噪声数值模拟及声振分析[J].计算机辅助工程,2015,24(4):48-51.Zhu Ying,Ma Lin,Dong Longlei.Jet flow noise numerical simulation and acoustic-vibration analysis of rocket engine[J].Computer Aided Engineering,2015,24(4):48-51.
[9] 李军.单兵火箭燃气射流冲击噪声场的形成与发展[J].南京理工大学学报,2006,30(6):679-683.Li Jun.Forming and developing of impact jet noise flow field of individual rocket[J].Journal of Nanjing University of Science and Technology,2006,30(6):679-683.
[10] 樊孝峰,王江峰,赵法明.Roe格式在多组元燃烧流场数值模拟中的应用[J].南京航空航天大学学报,2016,48(3):347-351.Fan Xiaofeng,Wang Jiangfeng,Zhao Faming.Numerical simulation of multi-component reacting flow using Roe scheme[J].Journal of Nanjing University of Aeronautics & Astronautics,2016,48(3):347-351.
[11] Egorov Y,Menter F.Development and application of SST-SAS turbulence model in the DESIDER project[C]//Advances in Hybrid RANS-LES Modelling.Heidelberg,Berlin,Germany:Springer,2008:261-270.
[12] Younsi M,Djerrada A,Belamri T,et al.Application of the SAS turbulence model to predict the unsteady flow field behaviour in a forward centrifugal fan[J].International Journal of Computational Fluid Dynamics,2008,22(9):639-648.
[13] 胡声超,鲍福廷,赵瑜.多喷管射流气动声学特性的数值研究[J].推进技术,2012,33(3):430-435.Hu Shengchao,Bao Futing,Zhao Yu.Numerical simulation for multi-jet aeroacoustics[J].Journal of Propulsion Technology,2012,33(3):430-435.