共轴刚性旋翼悬停状态气动干扰对噪声特性影响分析

江露生; 李尚斌; 邱逢昌; 樊枫; 黄水林

doi:10.13224/j.cnki.jasp.20220591

共轴刚性旋翼悬停状态气动干扰对噪声特性影响分析

doi: 10.13224/j.cnki.jasp.20220591

中国直升机设计研究所直升机动力学全国重点实验室，江西景德镇 333001

基金项目: 航空基金（201957002004）

详细信息

作者简介:
江露生（1992-），男，工程师，硕士生，主要从事直升机旋翼空气动力学研究。E-mail：jiangls@avic.com

中图分类号: V211.52
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出版历程
- 收稿日期: 2022-08-15
- 网络出版日期: 2023-12-13

Analysis on influence of aerodynamic interference on noise characteristics of coaxial rigid rotor in hover

National Key Laboratory of Helicopter Aeromechanics，China Helicopter Research and Development Institute，Jingdezhen Jiangxi 333001，China

摘要

摘要:
基于计算流体动力学（CFD）方法和噪声求解的FW-H（Ffowcs Williams-Hawkings）方程计算分析了共轴刚性旋翼在悬停状态下的气动噪声，并开展了气动干扰对噪声特性影响分析。结果表明：在悬停状态下，对于上下各四片桨叶的共轴刚性旋翼，桨叶表面压力随着桨叶旋转呈周期性变化，旋转一周出现8个小周期；声源的周期性变化导致在旋翼桨盘平面内，不同方向上的观测点的声压产生的“叠加效应”不一致，上、下旋翼桨叶交汇处的噪声水平要高于其他方位角；由于载荷的时变性导致在旋转轴方向上仍有明显的辐射噪声，在该方向上的噪声声压级明显要比单旋翼大得多。随着旋翼间距增大，双旋翼之间的干扰减小，桨叶表面的法向力波动减小，声辐射球上最大噪声声压级也明显减小。
- 共轴刚性旋翼 /
- 气动噪声 /
- 计算流体动力学（CFD） /
- FW-H（Ffowcs Williams-Hawkings）方程 /
- 悬停
Abstract:
Based on the computational fluid dynamics (CFD) method and noise solved FW-H (Ffowcs Williams-Hawkings) equation, the aeroacoustic noise of rigid coaxial rotor was calculated in hover, and the influence of aerodynamic interference on noise characteristics was analyzed. The study indicated that: in hover stage, the surface pressure of upper and lower rotor blades changed periodically with the rotation of the blade, and there were eight small cycles in one revolution; the periodic variation of the sound source led to inconsistent “superposition effect” produced by the sound pressure at observation points in different directions in the plane of the rotor disk, and the noise level at the intersection of upper and lower rotors was higher than that at other azimuths; due to the time-varying load, there was still significant radiation noise in the direction of the rotation axis, so the noise sound pressure level in this direction was much larger than that of single rotor. With the increase of rotor spacing, aerodynamic interference between twin rotors was reduced, and the normal force fluctuation of the maximum noise sound pressure level on the sound radiation sphere also decreased.
- rigid coaxial rotor /
- aeroacoustic /
- computational fluid dynamics (CFD) /
- FW-H (Ffowcs Williams-Hawkings) equation /
- hover

HTML

图 1 共轴双旋翼嵌套网格示意图

Figure 1. Coaxial dual-rotor overset grids

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图 2 桨叶表面压力计算与试验对比曲线（C_t,co=0.0163）

Figure 2. Comparison curve between calculation and test of blade surface pressure （C_t,co=0.0163）

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图 3 声压时间历程计算与试验对比

Figure 3. Comparison of sound pressure time history calculation and test

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图 4 悬停噪声状态观测点位置

Figure 4. Location of observation point

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图 5 双旋翼噪声声压时间历程（C_t,co=0.01741）

Figure 5. Coaxial dual-rotor’s sound pressure time history （C_t,co=0.01741）

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图 6 不同观测点声压级频谱（C_t,co=0.01741）

Figure 6. Sound pressure level spectrum （C_t,co=0.01741）

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图 7 单、双旋翼声压级随方位角变化曲线

Figure 7. Single-coaxial rotor sound pressure level variation curve with azimuth

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图 8 双旋翼声压级随方位角变化曲线

Figure 8. Coaxial rotor sound level variation curve with azimuth

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图 9 双旋翼噪声声压级云图

Figure 9. Cloud chart of sound pressure level of coaxial rotor

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图 10 单旋翼噪声声压级云图（C_t,sin=0.01182）

Figure 10. Cloud chart of sound pressure level of single rotor （C_t,sin=0.01182）

下载: 全尺寸图片幻灯片

图 11 共轴悬停状态旋翼桨盘载荷（C_t,co=0.01741）

Figure 11. Rotor disc load of coaxial rotor in hover （C_t,co=0.01741）

下载: 全尺寸图片幻灯片

图 12 单旋翼悬停状态旋翼桨盘载荷（C_t,sin=0.01182）

Figure 12. Rotor disc load of single rotor in hover （C_t,sin=0.01182）

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图 13 法向力系数对比曲线

Figure 13. Comparison curve of normal force coefficient

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图 14 桨叶表面点压力系数

Figure 14. Point pressure coefficient of blade surface

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图 15 不同旋翼间距的剖面法向力系数曲线

Figure 15. Section normal force coefficient of different rotor spacings

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图 16 不同旋翼间距的噪声声压时间历程

Figure 16. Sound pressure time history of different rotor spacings

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图 17 不同旋翼间距总噪声声压级云图

Figure 17. Cloud chart of sound pressure level of different rotor spacings

下载: 全尺寸图片幻灯片

表 1 基准旋翼参数

Table 1. Rotor parameters

旋翼参数	数值及说明
桨叶半径R/m	1
桨叶片数N	4+4
上下旋翼间距	0.14R
转速/（r/min）	1920
翼型	NACA0026、NACA0020、NACA0012
扭转分布	−12°/R
平面形状	矩形
初始方位角差/（°）	0

下载: 导出CSV

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