王阳, 徐国华, 招启军. 基于非结构网格CFD技术的旋翼气动噪声计算方法研究[J]. 空气动力学学报, 2011, 29(5): 559-566. DOI: 130.25/j.issn.0258-1825.2011.05.005
引用本文: 王阳, 徐国华, 招启军. 基于非结构网格CFD技术的旋翼气动噪声计算方法研究[J]. 空气动力学学报, 2011, 29(5): 559-566. DOI: 130.25/j.issn.0258-1825.2011.05.005
WANG Yang, XU Guo-hua, ZHAO Qi-jun. Numerical method for predicting rotor aerodynamic noise based on unstructured-grid CFD technology[J]. ACTA AERODYNAMICA SINICA, 2011, 29(5): 559-566. DOI: 130.25/j.issn.0258-1825.2011.05.005
Citation: WANG Yang, XU Guo-hua, ZHAO Qi-jun. Numerical method for predicting rotor aerodynamic noise based on unstructured-grid CFD technology[J]. ACTA AERODYNAMICA SINICA, 2011, 29(5): 559-566. DOI: 130.25/j.issn.0258-1825.2011.05.005

基于非结构网格CFD技术的旋翼气动噪声计算方法研究

Numerical method for predicting rotor aerodynamic noise based on unstructured-grid CFD technology

  • 摘要: 将基于非结构网格技术的旋翼流场CFD计算方法与基于FW-H和Kirchhoff方程的声学方法相结合,建立了一套既适合于直升机旋翼厚度、载荷和桨涡干扰噪声,又适合于跨声速高速脉冲噪声的综合计算模型。为提高旋翼流场及桨叶表面气动载荷计算的精度,主控方程的求解采用了三维可压非定常的N-S方程,网格划分则使用非结构运动嵌套网格方法。在噪声计算中,通过FW-H方法计算旋翼的厚度噪声和载荷噪声,并选取能够包含流场非线性区域的旋转面作为Kirchhoff积分面,由Kirchhoff方法计算包含四极子项的高速脉冲噪声。应用该模型,以AH-1旋翼为算例,计算了不同飞行状态下的旋翼气动噪声,并与可得到的试验结果进行比较,验证了方法的有效性。然后,着重对两种声学方法对计算结果的影响进行了对比研究,并分析了旋翼厚度噪声、载荷噪声和四极子噪声的特性。

     

    Abstract: Abstract A comprehensive computational model, coupling the rotor CFD method based on unstructured mesh and the acoustic methods based on FW-H and Kirchhoff equations, is established to calculate the thickness, loading noise and bladevortex interaction noise as well as the transonic HSI noise of helicopter rotor. In order to improve the calculation accuracy of aerodynamic loading on blade surface, the N-S equations are used to solve the flowfield around the rotor, and the unstructured grid is employed to model blade shape well. The thickness and loading noise of rotors are calculated based on the FW-H method, and the high speed impulsive noise including quadrupole term is calculatedbased on the Kirchhoff method at the same time. By this method developed, the acoustic calculations are performed for the AH1 rotor at different flight conditions, and the good correlations with available measured data demonstrate the validation of this method. Then, the influence of the two noise prediction methods on calculated results are emphatically investigated, and the characteristics of the thickness, loading and quadrupole noise are also analyzed.

     

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