Numerical Simulation for Multi-Jet Aeroacoustics

Journal of Propulsion Technology ›› 2012, Vol. 33 ›› Issue (3): 430-435.

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Numerical Simulation for Multi-Jet Aeroacoustics

College of Astronautics, Northwestern Polytechnical University, Xi’an 710072, China;College of Astronautics, Northwestern Polytechnical University, Xi’an 710072, China;College of Astronautics, Northwestern Polytechnical University, Xi’an 710072, China

Published:2021-08-15

多喷管射流气动声学特性的数值研究

胡声超,鲍福廷,赵瑜

西北工业大学航天学院,陕西西安 710072;西北工业大学航天学院,陕西西安 710072;西北工业大学航天学院,陕西西安 710072

作者简介:胡声超(1984—),男,博士生,研究领域为固体火箭燃气射流噪声。E-mail:hushengchao@mail.nwpu.edu.cn
基金资助:
国家自然科学基金(51005179)。

Abstract

Abstract: Large Eddy Simulation (LES) with Dynamic Smagorinsky Sub-Grid Model (SGS) was applied to simulate the 3-D unsteady supersonic hot multi-jet flow. Based on the results of the simulation, far field aeroacoustics of multi-jet were predicted by the Ffowcs Williams-Hawkings(FW-H) surface integral method and the results were compared with single nozzle. It shows that the flow field of multi-jet is complicated and the sound fields are not just a simple superposition of single nozzle. Some new characteristics are shown up. It changes not only the Overall Sound Pressure (OASPL) profile, but also the direction of radiation from 50° to 30°.

Key words: Multi-nozzles; Jet flow; Aeroacoustics; Numerical simulation; Large eddy simulation (LES)

摘要： 采用大涡模拟结合动力Smagorinsky亚格子模型对四喷管超声速高温射流进行了三维非稳态数值模拟。基于非稳态计算的结果,利用FW-H面积分方法对四喷管射流远场的声学特性进行计算,并将结果与单喷管得到的结果进行对比。结果表明,多喷管射流形成了复杂的流场,其产生的气动声场并不仅仅是单喷管简单的叠加,由于四股射流之间的相互影响使得声场也产生了新的特点,不但表现在总声压级数值上,还对改变了射流噪声辐射的指向性,最大声压级的位置由原来的50°左右变化到30°。

关键词: 多喷管;射流流场;气动声学;数值模拟;大涡模拟

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.

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Numerical Simulation for Multi-Jet Aeroacoustics

多喷管射流气动声学特性的数值研究

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