分开排气式喷管喷流噪声预测及试验研究

doi:10.7527/S1000-6893.2015.0257

流体力学与飞行力学

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分开排气式喷管喷流噪声预测及试验研究

吴飞¹, 邵万仁¹, 何敬玉², 李晓东², 王德友¹

1. 中航工业沈阳发动机设计研究所, 沈阳 110015;
2. 北京航空航天大学能源与动力学院, 北京 100083

收稿日期:2015-04-07 修回日期:2015-09-16 出版日期:2016-06-15 发布日期:2015-10-16
通讯作者: 吴飞男,硕士,工程师。主要研究方向:喷管及排气装置设计、喷流噪声抑制技术。Tel.:024-24281489 E-mail:wf606_2011@163.com E-mail:wf606_2011@163.com
作者简介:邵万仁男,博士,研究员。主要研究方向:喷流噪声抑制技术。Tel.:024-24281538 E-mail:13591462786@163.com
基金资助:
国家"973"计划(2012CB720201)

Experimental and prediction research on jet noise for separated exhaust nozzle

WU Fei¹, SHAO Wanren¹, HE Jingyu², LI Xiaodong², WANG Deyou¹

1. AVIC Shenyang Aeroengine Design and Research Institute, Shenyang 110015, China;
2. School of Energy and Power Engineering, Beihang University, Beijing 100083, China

Received:2015-04-07 Revised:2015-09-16 Online:2016-06-15 Published:2015-10-16
Supported by:
National Basic Research Program of China(2012CB720201)

摘要/Abstract

摘要：

为揭示涡扇发动机分开排气式喷管喷流噪声的频谱分布和指向特性,对喷管缩比模型远声场喷流噪声进行了预测及试验研究,并开展了全尺寸喷管基准型及锯齿型喷流噪声的预测工作。结果表明:采用Tam & Auriault方法可以预测出喷流噪声的声压级值和空间指向分布,喷流噪声具有明显的指向性。与基准型喷管相比,锯齿型喷管具有良好的降噪效果;内外涵锯齿型喷管在中低频段的降噪效果优于内涵锯齿型喷管,在高频段的降噪效果差于内涵锯齿型喷管;在本文研究参数范围内,指向角小于88°时内外涵锯齿型喷管总声压级(OASPL)值高于内涵锯齿型喷管。

关键词: 分开排气式, 喷流噪声, Tam &, Auriault方法, 锯齿型, 总声压级(OASPL)

Abstract:

In order to reveal the distribution of frequency spectrum and directivity for the separated exhaust nozzle, prediction and experiment are conducted for scaled mode, then full-scale nozzle model of basic and chevron are calculated. The result shows that Tam & Auriault's jet noise prediction theory is used to predict the noise spectra and direction of far-field noise, and jet noise possesses obvious direction. Compared with basic nozzle, the reduced effect of jet noise with chevron is better. Chevrons are fixed only in primary nozzles which have worse ability of low-frequency noise reduction and the high-frequency noise increase by contrast with chevrons which are fixed in primary and bypass nozzles. The overall sound pressure level (OASPL) value of chevrons which are fixed only in primary nozzles is less than that of chevrons fixed in primary and bypass nozzles at the angle of directivity smaller than 88° in this paper.

Key words: separated exhaust, jet noise, Tam &, Auriault' method, chevron, overall sound pressure level (OASPL)

中图分类号:

V231.1

吴飞, 邵万仁, 何敬玉, 李晓东, 王德友. 分开排气式喷管喷流噪声预测及试验研究[J]. 航空学报, 2016, 37(6): 1790-1797.

WU Fei, SHAO Wanren, HE Jingyu, LI Xiaodong, WANG Deyou. Experimental and prediction research on jet noise for separated exhaust nozzle[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(6): 1790-1797.

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

分开排气式喷管喷流噪声预测及试验研究

Experimental and prediction research on jet noise for separated exhaust nozzle

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