摘要
为了研究喷管尺寸对火箭发动机喷流噪声声场分布的影响规律,采用LES与FW-H相结合的方法,针对不同喷管尺寸的高温燃气喷流气动声场进行了数值模拟,并分析了声场特性。数值结果表明,火箭发动机喷流远场噪声具有方向性,噪声声压级在离开喷流中心轴线40°处达到最大值;喷流噪声声场的声压级随着喷管尺寸的增大而增加。研究结果为不同尺寸的火箭发动机喷流噪声预测提供参考依据。
In order to predict the distribution of sound fields of the jet noise of a rocket engine,we performed the numerical simulation of the aerodynamic sound field of the noise of high-temperature jet of nozzles of different sizes and analyzed the characteristics of the sound field.Then,we designed the three types of nozzles with the same outlet Mach number but different sizes and simulated their jet noise and analyzed its sound field distribution and the effects of nozzle sizes on the jet noise of a rocket engine.The simulation results,given in Figs.5 through 9,and their analysis show preliminarily that：（1） the noise at the far field of the jet is directional;（2） the sound pressure level of the jet noise reaches maximum at the angle of 40°away from the jet center axis;（3） the sound pressure level of the jet noise sound field increases with increasing nozzle sizes.
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
2013年第3期345-349,共5页
Journal of Northwestern Polytechnical University
基金
国家自然科学基金(50976095)资助
关键词
火箭发动机
喷流噪声
数值模拟
大涡模拟
喷管尺寸
computer simulation
rocket nozzles
rocket engines
numerical methods
sound field
jet noise
nozzle size
