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论文:2020,Vol:38,Issue(6):1275-1283 |
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引用本文： |
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樊枫, 曹亚雄, 江露生, 林永峰. 直升机噪声声散射特性计算方法研究[J]. 西北工业大学学报 |
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FAN Feng, CAO Yaxiong, JIANG Lusheng, LIN Yongfeng. Research on Calculation Method for Acoustic Scattering of Helicopter Noise[J]. Northwestern polytechnical university |
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| 直升机噪声声散射特性计算方法研究 |
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| 樊枫, 曹亚雄, 江露生, 林永峰 |
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| 中国直升机设计研究所 直升机旋翼动力学国家级重点实验室, 江西 景德镇 333001 |
| 摘要: |
| 发展了直升机旋翼（尾桨）噪声与机身的声散射特性计算方法。首先，采用基于运动嵌套网格和RANS方程的旋翼CFD方法计算旋翼流场信息，为旋翼噪声计算提供气动数据；然后，采用FW-H方程来计算孤立旋翼的气动噪声特性，并应用G1A公式来计算旋翼噪声梯度，为噪声声散射分析提供边界条件；在此基础上，采用时域等效源方法计算散射声场，并与孤立旋翼声场进行叠加，最终得到考虑机身散射影响的总声场。最后，应用建立的声散射计算模型，针对旋翼/机身和尾桨/机身声散射效应进行了数值模拟，结果表明：机身对旋翼与尾桨高频噪声的散射影响较大，并且旋翼/机身以及尾桨/机身的间距越小，声散射效应越明显。 |
| 关键词:
声散射
旋翼
噪声
机身
直升机
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| Research on Calculation Method for Acoustic Scattering of Helicopter Noise |
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| FAN Feng, CAO Yaxiong, JIANG Lusheng, LIN Yongfeng |
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| Science and Technology on Rotorcraft Aeromechanics Laboratory, China Helicopter Research and Development Institute, Jingdezhen 333001, China |
| Abstract: |
| A new calculation method of helicopter rotor/fuselage acoustic scattering is developed. Firstly, a CFD analysis model is developed to simulate flow field of the rotor, which is based on the motional embedded grid system and RANS equations, and provides aerodynamic data for rotor noise calculation. Then, FW-H equations are employed to calculate the aeroacoustic characteristics of isolated rotor, and G 1A formulas are applied to calculate the rotor acoustic gradient to provide boundary condition for acoustic scattering. Based on these, the time-domain equivalent source method is applied to calculate acoustic scatter field, and the total acoustic field that considered the fuselage scatter is superposed by isolated rotor acoustics and the scatter one. Finally, the numerical simulations of helicopter main-rotor/fuselage and tail-rotor/fuselage scatter effect are conducted by using the developed models. The results indicate that the helicopter fuselage has important scatter effect on the high frequency acoustics of main rotor and tail rotor, and the acoustic scatter effect become more obvious with the smaller space between the main rotor (tail rotor) and fuselage. |
| Key words:
acoustic scatter
rotor
noise
fuselage
helicopter
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| 收稿日期: 2019-12-30
修回日期:
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| DOI: 10.1051/jnwpu/20203861275 |
| 通讯作者: 曹亚雄(1990-),中国直升机设计研究所工程师,主要从事直升机气动噪声研究。e-mail:caoyx@avic.com
Email：caoyx@avic.com |
| 作者简介: 樊枫(1987-),中国直升机设计研究所高级工程师,主要从事直升机空气动力学研究。
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