| 齿根倾斜锯齿尾缘叶片噪声控制实验 |
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| 引用本文： | 焦跃,杨爱玲,陈二云.齿根倾斜锯齿尾缘叶片噪声控制实验[J].航空动力学报,2019,34(1):189-194. |
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| 作者姓名： | 焦跃 杨爱玲 陈二云 |
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| 作者单位： | 上海理工大学能源与动力工程学院,上海200093;上海理工大学上海市动力工程多相流动与传热重点实验室,上海200093;上海理工大学能源与动力工程学院,上海200093;上海理工大学上海市动力工程多相流动与传热重点实验室,上海200093;上海理工大学能源与动力工程学院,上海200093;上海理工大学上海市动力工程多相流动与传热重点实验室,上海200093 |
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| 基金项目： | 国家自然科学基金（51106099）；上海市科委基地建设项目（13DZ2260900） |
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| 摘 要： | 针对NACA0018翼型传统锯齿尾缘的钝型齿根部,设计了一种具有齿根倾斜的新型锯齿尾缘,并采用实验方法研究了齿根倾斜角对翼型尾缘噪声的影响规律。研究结果表明,新型锯齿尾缘在大攻角范围内（12°~18°）,可使叶片噪声下降3.2~17.1dB,在小攻角范围,对中频范围出现的“驼峰”有抑制作用,且齿根倾斜角为30°的新型锯齿尾缘叶片消除了声压频谱的“驼峰”窄带峰,整体噪声下降0.2~1.5dB。
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| 关 键 词： | 尾缘噪声 锯齿尾缘 齿根倾斜 气动噪声 噪声测量 |
| 收稿时间： | 2018/1/11 0:00:00 |
Experiment on noise control of trailing edge serrations with sloping root |
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| Abstract: | A novel serration with sloping root was designed based on the traditional serrated trailing edge with blunt root on NACA0018 airfoil. The influence of sloping angle on trailing edge noise was studied by an experiment. It was found that the novel serrations can reduce the noise by 3.2-17.1dB at high angle of attack (12°-18°), and had a certain inhibitory effect on the hump shaped noise peak which appeared in the middle sound pressure spectrum at low angle of attack. When the sloping angle was 30°, the hump shaped noise peak was eliminated and the overall sound pressure level had a reduction of 0.2-1.5dB. |
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| Keywords: | trailing edge noise trailing edge serrations sloping root aero-acoustics noise measurement |
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