Analyses about impact mechanism of new type blade-tip on inhibiting rotor transonic acoustic characteristics
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摘要: 为研究不同形式的新型桨尖在抑制旋翼跨声速噪声特性方面的作用机理，以UH-1H模型旋翼为基准，开展了多种后掠和前掠桨尖对旋翼高速脉冲噪声特性的数值分析研究。采用积分形式的可压缩雷诺平均Navier-Stokes（RANS）方程作为旋翼流场求解控制方程，时间推进方法采用高效的隐式LU-SGS格式，空间方向采用高精度的Roe-MUSCL格式，湍流模型选用Baldwin-Lomax模型。在CFD方法验证基础上，采用基于可穿透旋转积分面的鲁棒性较好的FW-H_pds方程来求解旋翼高速脉冲（high-speed impulsive，HSI）噪声，并通过对UH-1H模型旋翼的跨声速噪声的计算，验证了噪声预测方法的有效性。在此基础上，研究了在不同桨尖马赫数下的旋翼桨尖附近的离域化（delocalization）现象以及高速脉冲噪声特性，通过四极子噪声和单极子噪声的对比分析，揭示了旋翼跨声速噪声产生机理。然后，着重研究了不同外形参数的后掠和前掠桨尖旋翼在抑制旋翼跨声速特性方面的影响规律。计算结果表明：随着桨尖马赫数的增加，旋翼高速脉冲噪声辐射愈加强烈，离域化现象愈加明显；后掠和前掠桨尖旋翼均可以不同程度地减弱激波强度，能有效抑制离域化现象的产生，从而降低旋翼跨声速噪声水平；前掠桨尖旋翼还可以驱使激波位置向桨叶内侧移动，减弱其对桨叶外部空间区域的影响，能更有效地抑制离域化现象的产生。
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关键词:
- 旋翼 /
- 高速脉冲噪声 /
- 离域化 /
- 新型桨尖 /
- Navier-Stokes方程 /
- FW-H_pds方程
Abstract: To investigate the effects of different new types of blade-tip on transonic acoustic characteristics of a helicopter rotor, numerical analyses about the impacts of blade-tips on the high-speed impulsive (HSI) noise characteristics have been carried out by taking the UH-1H model rotor as baseline. A CFD simulation method is developed by solving the compressible Reynolds-averaged Navier-Stokes (RANS) equations with Baldwin-Lomax turbulence model, and a high-precision Roe-MUSCL scheme and high-efficiency implicit LU-SGS scheme are employed for spatial and temporal discretization respectively. Based on the validation of CFD method, a robust FW-H_pds method based on the penetrable data surface is established for predicting rotor HSI noise, and the transonic acoustic characteristics of UH-1H model rotor have been simulated to verify the effectiveness of the present method. Based on these methods, the influences of Mach number on the phenomenon named "delocalization" nearby the blade tip and the HSI noise characteristics are analyzed, and the generation mechanism of transonic noise is revealed by the comparisons of the monopole noise and quadrupole noise. Then, the influences of both sweep-back and sweep-forward blade-tip on inhibiting rotor transonic acoustic characteristics are analyzed at a transonic state respectively. The numerical results indicate that the serious delocalization phenomenon and the HSI noise radiation occur strongly with the increase of the blade-tip Mach number. Compared with rectangular blade, the rotors with sweep-back or sweep-forward blade-tip can reduce HSI noise level at a transonic state by suppressing the supersonic flow and delaying the occurrence of delocalization effects. Furthermore, sweep-forward blade-tip has a more remarkable effect on inhibiting delocalization effects by driving supersonic flow region to move to inside of blade.-
Key words:
- rotor /
- high-speed impulsive noise /
- delocalization /
- new type blade-tip /
- Navier-Stokes equations /
- FW-H_pds equations
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图 2 UH-60A旋翼悬停性能的计算值和试验值的比较
Figure 2. Comparison of the calculated performance of UH-60A rotor with experimental data
图 3 UH-1H模型旋翼不同桨尖马赫数下的声压时间历程
Figure 3. Time history of sound pressure of UH-1H rotor model at various tip Mach number
图 4 UH-1H模型旋翼不同桨尖马赫数下的负压峰值
Figure 4. Negative peak pressure of UH-1H rotor model at various tip Mach number
图 5 不同桨尖马赫数时的桨盘平面超声速流动区域
Figure 5. Supersonic region on the rotor plane at various tip Mach number
图 6 不同后掠桨尖旋翼的噪声负压峰值比较
Figure 6. Comparisons of negative peak pressure of rotors with various sweep-back blades
图 7 不同后掠桨叶的等马赫数云图
Figure 7. Contour maps of Mach number distributions of various sweep-back blades
图 8 不同前掠桨尖旋翼的噪声负压峰值比较
Figure 8. Comparisons of negative peak pressure of rotors with various sweep-forward blades
图 9 不同前掠桨叶的等马赫数云图
Figure 9. Contour maps of Mach number distributions of various sweep-forward blades
表 1 后掠桨叶参数和代号
Table 1. Parameters and codes of sweep-back blade
10° 20° 30° 0.95R SB01 SB02 SB03 0.85R SB04 SB05 SB06 
下载: 导出CSV
表 2 前掠桨叶参数和代号
Table 2. Parameters and codes of sweep-forward blade
10° 20° 30° 0.95R SF01 SF02 SF03 0.85R SF04 SF05 SF06
下载: 导出CSV
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