| 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 |
| DOI： |
| 分类号: |
| 基金项目:国家自然科学基金(51005179)。 |
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| Numerical Simulation for Multi-Jet Aeroacoustics |
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HU Sheng-chao, BAO Fu-ting, ZHAO Yu
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College of Astronautics, Northwestern Polytechnical University, Xi’an 710072, China
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| 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) |
