| 喷流气动噪声仿真计算 |
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| 引用本文： | 刘兴强,黄文超,李红丽.喷流气动噪声仿真计算[J].科学技术与工程,2019,19(22):338-342. |
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| 作者姓名： | 刘兴强 黄文超 李红丽 |
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| 作者单位： | 中国飞机强度研究所 西安 710065,中国飞机强度研究所 西安 710065,中国飞机强度研究所 西安 710065 |
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| 基金项目： | 锯齿形喷口降噪特性研究（2014ZD23009） |
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| 摘 要： | 针对内外涵分开双喷流的噪声问题进行了仿真计算研究。计算采用"CFD+CAA"的混合方法,流场计算采用大涡模拟(LES),捕捉流场中的主要噪声源;声场计算采用FW-H(Ffowcs WilliamsHawkings equation)方程积分得到远场噪声信息。为了降低喷流噪声,在内涵安装了锯齿形喷嘴。安装锯齿形喷嘴后,内外涵气流掺混增强,增加了内涵的喷流有效面积,使得中低频噪声降低,高频噪声略有增加,总体降噪量3～5 d B。喷流噪声具有明显的指向性,喷流下游噪声明显高于上游,总体指向喷流下游。
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| 关 键 词： | 喷流噪声，锯齿形喷嘴，气动噪声计算，大涡模拟，FW-H方程 |
| 收稿时间： | 2019/1/27 0:00:00 |
| 修稿时间： | 2019/3/9 0:00:00 |
The simulation of separated exhaust jet noise |
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| LIU Xingqiang,HUANG Wenchao and LI Hongli.The simulation of separated exhaust jet noise[J].Science Technology and Engineering,2019,19(22):338-342. |
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| Authors: | LIU Xingqiang HUANG Wenchao and LI Hongli |
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| Institution: | AVIC Aircraft Strength Research Institute,Xi''an,710065,AVIC Aircraft Strength Research Institute,Xi''an,710065,AVIC Aircraft Strength Research Institute,Xi''an,710065 |
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| Abstract: | Simulation was launched in this paper to study the noise characterristics of esparated exhaust jet. The accurate transitent flow that contains all the information of noise source was gotten via Large Eddy Simulation (LES). Basing on the results of flow caculation, acoustic field will be obtained by solving the Ffwocs Williams&Hawking (FW-H) equation. Chevrons nozzle is installed on the core duct to reduce the jet noise. This induces core and fan flow mixed rapidly and increase the aera of the core flow cross-section. Basing on this mixer the mid and low frequency noise attenuted, high-frequency has a modest growth. And the toatl sound pressure level has a 3dB-5dB reduction. The directivity of jet noise is obvious, the downstream noise is intenser than upstream. |
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| Keywords: | jet noise chevron nozzle computational aeroacoustics large eddy simulation FW-H equations |
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