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 2nd 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.
作者
盛英华
沈林
曹文斌
乐贵高
邢成龙
Sheng Yinghua;Shen Lin;Cao Wenbin;Le Guigao;Xing Chenglong(Aerospace System Engineering Shanghai,Shanghai 201109,China;School of Mechanical Engineering,Nanjing University of Science and Technology,Nanjing 210094,China)
出处
《南京理工大学学报》
EI
CAS
CSCD
北大核心
2019年第2期165-169,176,共6页
Journal of Nanjing University of Science and Technology
