Numerical investigation of noise reduction law and acoustic mecha-nism of the sweepback propfan
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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。
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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图 5 巡航状态下前桨95%叶高马赫数分布
Figure 5. Mach number distributions of front blade at 95% span at cruise condition
图 6 巡航状态下50%叶高马赫数分布
Figure 6. Mach number distributions at 50% span at cruise condition
图 7 起飞状态下50%叶高马赫数分布
Figure 7. Mach number distributions at 50% span at take-off condition
图 8 起飞状态下95%叶高前桨马赫数分布
Figure 8. Mach number distributions of front blade at 95% span at take-off condition
图 9 起飞状态下95%叶高后桨马赫数分布
Figure 9. Mach number distributions of rear blade at 95% span at take-off condition
图 10 起飞状态桨叶表面静压的1阶谐波
Figure 10. The 1st harmonic pressure distributions of blade surface at take-off condition
图 11 起飞状态后桨吸力面静压的1阶谐波
Figure 11. The 1st harmonic pressure distributions of rear blade suction-surface at take-off condition
图 12 起飞状态后桨吸力面静压的2阶谐波
Figure 12. The 2nd harmonic pressure distributions of rear blade suction-surface at take-off condition
图 13 起飞状态后桨吸力面静压的3阶谐波
Figure 13. The 3rd harmonic pressure distributions of rear blade suction-surface at take-off condition
图 14 对转桨扇噪声频谱（后掠角30°）
Figure 14. Noise spectrum of the propfan （backward sweep angle 30°）
图 15 对转桨扇声压级指向性（sweep30）
Figure 15. Sound pressure level directivity of the propfan (sweep30)
图 16 不同后掠角下对转桨扇声压级指向性
Figure 16. Sound pressure level directivity of the propfan with different backward sweep angle
图 17 不同后掠角下70°角向位置桨扇噪声频谱对比
Figure 17. Noise spectrum of the propfan with different backward sweep angle at 70° angular position
图 18 不同后掠角下桨扇桨叶通过频率的声压级指向性
Figure 18. Sound pressure level directivity of the propfan blade passing frequency with different backward sweep angle
图 19 不同后掠角下前后桨干涉声压级指向性
Figure 19. Interference sound pressure level directivity of the propfan with different backward sweep angle
图 20 不同后掠角下160°角向位置桨扇噪声频谱
Figure 20. Noise spectrum of the propfan with different backward sweep angle at 160° angular position
图 21 不同后掠角下30°角向位置桨扇噪声频谱
Figure 21. Noise spectrum of the propfan with different backward sweep angle at 30° angular position
图 22 不同后掠角下前后桨干涉声压级指向性
Figure 22. Interference sound pressure level directivity of the propfan with different backward sweep angle
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