| 桨扇后掠降噪规律及声学机理数值研究 |
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| 引用本文： | 贺象,赵振国,舒太波,彭学敏.桨扇后掠降噪规律及声学机理数值研究[J].航空动力学报,2023,38(4):939-948. |
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| 作者姓名： | 贺象 赵振国 舒太波 彭学敏 |
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| 作者单位： | 中国航发湖南动力机械研究所中小型航空发动机叶轮机械湖南省重点实验室，湖南 株洲 412002 |
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| 基金项目： | 湖南创新型省份建设专项经费（2020RC3096） |
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| 摘 要： | 结合三维流场数值模拟方法和声学Ffowcs Williams-Hawkings方程声类比方法，对对转桨扇流动及声学特征进行仿真分析，研究了桨叶后掠角对对转桨扇的气动性能和气动噪声的影响规律。结果表明：对转桨扇桨叶后掠角从0°增加至40°，高速巡航状态推进效率可提高接近1.5个百分点，起飞状态推进效率提升不大；桨扇噪声大小与后排桨叶吸力面压力脉动强度有直接关系，增大桨扇桨叶后掠角可明显降低压力脉动强度，从而降低起飞状态下对转桨扇整个角向范围内的噪声大小；在噪声最大的75°角向位置，后掠角从0°增至40°声压级降低达3 dB以上。
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| 关 键 词： | 对转桨扇 桨叶后掠角 Ffowcs Williams-Hawkings方法 气动性能 压力脉动强度 噪声指向性 |
| 收稿时间： | 2021-05-06 |
Numerical investigation of noise reduction law and acoustic mecha-nism of the sweepback propfan |
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| Institution: | Hunan Key Laboratory of Turbomachinery on Small and Medium Aero-Engine， Hunan Aviation Powerplant Research Institute， Aero Engine Corporation of China，Zhuzhou Hunan 412002，China |
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| Abstract: | The propfan flow-field and acoustic features were investigated by combining the 3D numerical simulation with Ffowcs Williams-Hawkings equation. And the effects of propfan sweepback angle on aerodynamic performance and noise level were studied. It indicated that, with propfan sweepback angle increasing from 0° to 40°, the thrust efficiency was promoted about 1.5 percentage points at the high speed cruise condition but slightly at the take-off condition. The propfan noise level was directly related to the pressure fluctuation intensity of the rear blade suction surface. With the increase of sweepback angle, the pressure fluctuation intensity decreased, and then the noise level in all angular positions was reduced at the take-off condition. At the 75° angular position with the maximum sound pressure level, the sound pressure level decrease by more than 3 dB with propfan sweepback angle increasing from 0° to 40°. |
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