摘要
通过大涡模拟LES,对小型火箭发动机加长喷管形成的超声速射流进行三维瞬态数值模拟,选择适当封闭声源面,采用FW-H声学模型和傅里叶变换得到射流噪声声压级和频域的空间分布。研究结果表明:各个监测点的总声压级均达100 dB以上,总声压级随喷管出口距离以及与射流轴线夹角增大减小,且减幅随距离增大变小;总声压级在靠近出口时近轴线越大,而距离在400 mm以上时在40°方向最大,表现出指向性;各采集点的声压分布具有宽频性,且各采集点声压峰值频率均分布在4000~5000 Hz,表现出空间一致性。
Large-eddy simulation(LES)has been used to investigate these jet noise of the extended nozzle.A permeable Ffowcs Williams Hawkings(FWH)surface enclosing the jet is used to predict far-field noise from the simulated flow-field.The results show that the overall sound pressure level(OASPL)is more than 100 dB at each receiver,and it decreases with the increase of the distance to nozzle and the angle with the jet axis.And the reduction decreases with the increase of the distance.And when the distance is more than 400 mm,the OASPL of receiver where the angel is 40°is the maximum directly at the each same distance.The distribution of sound pressure level(SPL)is broadband,and the peak frequency of the SPL is in the range of 4000 to 5000 Hz similarly for every receiver.
作者
范珂华
查柏林
周伟
王金金
FAN Kehua;ZHA Bailin;ZHOU Wei;WANG Jinjin(Rocket Force University of Engineering, Xi’an 710025, China;Project Management Center of PLA Rocket Force Equipment Department, Beijing 100085, China)
出处
《兵器装备工程学报》
CSCD
北大核心
2022年第4期55-60,共6页
Journal of Ordnance Equipment Engineering
基金
国家自然科学基金青年基金项目(52003296)
陕西省自然科学基础研究计划资助项目(2020JQ-488)
陕西省表面技术重点实验室基金项目(2019SZS-09)。
