Buzz-saw noise considering blade tip clearance and blade variations
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摘要:
以NASA Rotor 67为原型，建立了3种叶尖间隙叠加随机安装角扰动的跨声速风扇转子。通过全环数值模拟和基于叶栅假设的理论推导，先后分析了叶尖间隙单一因素以及叶尖间隙与叶片安装角扰动共同作用对激波噪声的影响规律。结果表明：①叶尖间隙导致的泄漏流与前缘激波噪声存在耦合关系，叶尖间隙增大引发泄漏流增强，导致流道堵塞增加，间接降低了叶片前缘激波强度和关联的激波噪声；②叶尖泄漏流诱导的激波噪声分量需要在叶片几何扰动共同作用下才能向远场传播；③建立了一个考虑叶尖间隙和叶片安装角扰动的风扇激波噪声预测模型，通过数值模拟验证表明该预测模型具有较高的精度。
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关键词:
- 风扇激波噪声 /
- 叶尖泄漏流 /
- 叶片几何扰动 /
- 准三维叶尖模型 /
- 泄漏流与激波噪声耦合效应
Abstract:Rotors with three tip clearances, as well as random stagger disturbances, were established with NASA Rotor 67 as the prototype. Through full-annulus numerical simulations and theoretical derivations based on cascade assumptions, the effects of blade tip clearance and the coupling effects of blade tip clearance and blade stagger disturbances on buzz-saw noise were analyzed. The results showed that: (1) there was a coupling relationship between the leakage flow induced by blade tip clearance and the generation of forward propagating buzz-saw noise. As the blade tip clearance increased, the leakage flow was enhanced, leading to channel blockage, indirectly reducing the shock intensity and corresponding buzz-saw noise; (2) the extra component of buzz-saw noise generated by tip leakage flows can only propagate to the far field by coupling with the blade variations; (3) a theoretical model was established to account for the coupling effect of tip clearance and blade variations on buzz-saw noise. The validation by numerical simulations showed that this model had relatively high accuracy for the analysis of buzz-saw noise.
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图 7 近峰值效率工况轴向速度沿径向分布对比
Figure 7. Comparison of the axial velocity along the radius at near peak operating condition with experimental data
图 8 不同叶尖间隙下径向99%位置处静压分布
Figure 8. Static pressure distribution at 99% radius with different blade tip clearances
图 10 Rotor 67子午面相对马赫数和相关流动结构
Figure 10. Relative Mach number on the meridional plane and related flow structures in Rotor 67
图 11 S1截面两个径向位置处频谱
Figure 11. Spectra of buzz-saw noise at two radial positions on observing plane S1
图 12 S3截面径向99%位置处频谱
Figure 12. Spectra of buzz-saw noise at 99% radius observing plane S3
图 14 Rotor SV叶片前缘径向静压梯度分布
Figure 14. Static pressure gradient along the radius in Rotor SV leading-edge
图 16 2.0δ叶尖间隙Rotor SV叶尖泄漏涡结构
Figure 16. Structures of tip leakage vortices in Rotor SV with 2.0δ blade tip clearance
图 17 Rotor SV S1截面不同径向位置频谱分布
Figure 17. Spectra at different radial positions on plane S1 in Rotor SV
图 18 Rotor SV S1～S3截面机匣附近频谱分布
Figure 18. Spectra near the shroud on plane S1—S3 in Rotor SV
图 19 不同叶尖间隙Rotor SV S3截面机匣附近频谱分布
Figure 19. Spectra near the shroud on plane S3 in Rotor SV with different blade tip clearances
图 21 Rotor 67堵塞因子随叶尖间隙变化
Figure 21. Blockage coefficient of Rotor 67 with respect to blade tip clearance
图 22 叶尖泄漏流对前缘激波作用模型
Figure 22. Physical model for the interaction between tip leakage flows and leading-edge shock waves
图 23 激波脱体距离随叶尖间隙变化
Figure 23. Shock detachment ratio with respect to blade tip clearance
图 24 激波脱体距离随安装角扰动变化
Figure 24. Shock detachment ratio with respect to stagger variation
图 25 数值和理论推导归一化激波强度对比
Figure 25. Comparison of the normalized shock strength from the numerical and theoretical predictions
图 26 数值和理论推导归一化激波噪声频谱对比
Figure 26. Comparison of the normalized spectra from the numerical and theoretical predictions
表 1 22个叶片上随机安装角扰动
Table 1. Random stagger variations at 22 fan blades
（°） 叶片编号 扰动量 叶片编号 扰动量 1 0 12 0.2 2 0.2 13 −0.1 3 0.15 14 0.1 4 0.13 15 −0.14 5 −0.12 16 0.15 6 −0.13 17 −0.15 7 0.19 18 −0.16 8 0.17 19 −0.1 9 −0.1 20 0.1 10 0.11 21 0.1 11 0.1 22 −0.11 
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表 2 实验和模拟数据对比
Table 2. Comparison between simulation and experiment
数据来源 总压比 质量流量/（kg/s） 效率 实验 1.630 33.25 0.908 模拟 1.621 33.25 0.898
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