Research on numerical simulation of flow field and sound field of counter-rotating propeller
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摘要:
采用非线性谐波法耦合FW-H方程的混合噪声数值模拟方法，对某11×9的对转螺旋桨模型的气动力与噪声开展了数值模拟研究。结果表明：在起飞阶段，与单转子螺旋桨相比，对转螺旋桨的主要噪声源是由前排螺旋桨产生的叶尖涡、前缘涡和尾迹涡等涡系与后排螺旋桨相互作用产生的干涉噪声，后排螺旋桨上的非定常压力波动是干涉噪声的主要贡献源；在干涉噪声频率处，前排螺旋桨的噪声主要向下游辐射，后排螺旋桨的噪声主要向上游辐射。此外，还研究了不同积分面对对转螺旋桨噪声计算结果的影响。相比于固体壁面FW-H积分面，可穿透FW-H积分面的计算结果更接近试验数据，但是不同的积分面对转子单独噪声基本没有影响；上游积分面的变化对对转螺旋桨的噪声影响很小，但是下游积分面的变化对干涉噪声影响较大。
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关键词:
- 对转螺旋桨 /
- 气动性能 /
- 干涉噪声 /
- 固体壁面FW-H积分面 /
- 可穿透FW-H积分面
Abstract:The hybrid noise numerical simulation method of nonlinear harmonic method coupled with FW-H equation was used to study the aerodynamic force and noise of a 11×9 counter-rotating propeller model. The results of the study showed that: during the takeoff phase, the main noise source of the counter-rotating propeller was the interference noise generated by the interaction of the vortex systems such as the blade tip vortex, leading edge vortex and trailing vortex generated by the front propeller with the rear propeller, and the non-constant pressure fluctuation on the rear propeller was the main contributor to the interference noise. At the frequencies where interference noise appeared, the noise of the front propeller radiated mainly downstream, and the noise of the rear propeller radiated mainly upstream. Compared with the solid FW-H surface, the calculation results of the porous FW-H surface were closer to the experimental data. Different integration surfaces had little effect on the noise of the counter-rotating propeller, but the variation of the downstream integration surface had a greater effect on the interference noise.
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图 1 对转螺旋桨的配置和几何布局
Figure 1. Contra rotating propeller configuration and geometric layout
图 5 前排螺旋桨50%叶高处表面静压
Figure 5. Surface static pressure at 50% blade height of front propeller
图 10 单转子螺旋桨和对转螺旋桨不同截面位置示意图
Figure 10. Schematic diagram of different cross-section position of single rotor propeller and counter-rotating propeller
图 11 单转子螺旋桨和对转螺旋桨轴向时均速度的径向分布
Figure 11. Time-averaged axial and radial velocity profiles of single rotor propeller and counter-rotating propeller
图 12 单转子螺旋桨和对转螺旋桨径向时均速度的径向分布
Figure 12. Time-averaged radial velocity profiles of single rotor propeller and counter-rotating propeller
图 15 前排叶片吸力面和压力面压力系数云图
Figure 15. Pressure coefficient contour of suction and pressure surfaces of front blades
图 16 后排叶片吸力面压力系数云图
Figure 16. Pressure coefficient contour of suction surface of rear blades
图 17 不同叶高处叶片表面压力系数分布
Figure 17. Surface pressure coefficient at different blade heights
图 18 前排螺旋桨后Z/R=0.15和Z/R=0.3截面及速度云图
Figure 18. Z/R=0.15 and Z/R=0.3 cross-section and velocity contour after front propeller
图 19 Z/R=0.15处不同时刻静压云图
Figure 19. Static pressure contour at Z/R=0.15 at different moments
图 21 前排螺旋桨叶尖涡系与后排螺旋桨相互作用
Figure 21. Interaction between tip vortex system of front propeller and rear propeller
图 22 前、后排转子和轮毂表面静压及一阶谐波压力云图
Figure 22. Static pressure and first-order harmonic pressure contours of front and rear rotors and hub surface
图 26 BPF1和BPF2处前排螺旋桨、后排螺旋桨和对转螺旋桨噪声指向性
Figure 26. Acoustic directivity of front and rear propellers and counter-rotating propeller at BPF1 and BPF2
图 27 BPF1+BPF2和2BPF1+BPF2处前排螺旋桨、后排螺旋桨和对转螺旋桨噪声指向性
Figure 27. Acoustic directivity of front and rear propellers and counter-rotating propeller at BPF1+BPF2 and 2BPF1+BPF2
图 29 BPF1和BPF2处不同积分面的噪声指向性
Figure 29. Acoustic directivity of different integral surface at BPF1 and BPF2
图 30 BPF1+BPF2处（2553.63 Hz）不同积分面噪声指向性
Figure 30. Acoustic directivity of different integral surface at BPF1+BPF2 （2553.63 Hz）
图 31 2BPF1+BPF2处（3953.01 Hz）不同积分面噪声指向性
Figure 31. Different integral surface acoustic directivity at 2BPF1+BPF2 （3953.01 Hz）
表 1 对转螺旋桨的设计参数
Table 1. Contra rotating propeller design parameters
参数 数值 前排螺旋桨 后排螺旋桨 直径D/m 0.616 0.606 叶片数 11 9 转速/（r/min） −7633 7695 轮毂比 0.59 0.56 
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表 2 网格无关性验证
Table 2. Mesh independence verification
网格 前排
推力/N后排
推力/N前排
误差/%后排
误差/%粗糙网格
（500万）1514.7 1221.3 1.10 2.80 中等网格
（790万）1488.3 1200.6 0.06 1.00 精细网格
（1250万）1497.1 1188.0 超精细网格
（1975万）1490.0 1183.5 0.04 0.38
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