基于URANS/TPP模型的风扇转静干涉单音噪声预测  

Fan rotor-stator interaction noise prediction based on URANS/TPP model

作　　者：蔡堉楠 纪良 李旦望 夏烨 倪臻 CAI Yunan;JI Liang;LI Danwang;XIA Ye;NI Zhen(Department of Advanced Technologies,AECC Commercial Aircraft Engine Co.,Ltd.,Shanghai 200241,China)

机构地区：[1]中国航发商用航空发动机有限责任公司先进技术研究部,上海200241

出　　处：《航空学报》2023年第22期170-181,共12页Acta Aeronautica et Astronautica Sinica

基　　金：国家科技重大专项(J2019-Ⅱ-0006-0026);上海市“科技创新行动计划”启明星项目(23YF1452000)。

摘　　要：为了解决风扇噪声三维高精度评估问题,基于非定常雷诺平均数值模拟(Unsteady Reynolds Average Numerical Simulation,URANS)模型和三平面压力(Triple Plane Pressure,TPP)模态匹配模型,发展了风扇转静干涉单音噪声数值预测方法。分析了URANS模型管道内单音计算的可行性,并建立了误差控制准则。在此基础上,采用URANS模型获得风扇非定常流场,同时基于TPP方法进行声源提取,得到管道内单音噪声的模态特性。基于国产某型大涵道比缩尺风扇试验数据,对模型准确性进行对比验证。结果表明,该模型能够进行转静干涉噪声的可靠预测。此外,进行了基于弯掠静子的低噪声叶片设计,并采用提出的数值模型分析了三维流场/声场,探究了基于叶型设计的转静干涉声源抑制机理,实现了对风扇低噪声设计的支撑。In order to solve the problem of three-dimensional high-precision evaluation of fan noise,a numerical pre⁃diction method for the fan rotor-stator interaction noise is successfully proposed based on the Unsteady Reynolds Aver⁃age Numerical Simulation(URANS)model and the Triple Plane Pressure(TPP)mode matching model.The feasibil⁃ity of the URANS model for tone noise calculation in the duct is analyzed,and an error control criterion is established.On this basis,the URANS model is used to obtain the unsteady flow field of the fan,and the noise source is extracted using the TPP mode matching method to obtain the modal characteristics of the noise in the duct.Based on the ex⁃perimental data of a large bypass ratio scaled fan,the accuracy of the model is compared and verified.The results show that the model is able to reliably predict the rotor-stator interaction noise.In addition,the design of low-noise blades based on the leaned and swept stator is carried out.The three-dimensional flow and acoustic fields are ana⁃lyzed based on the proposed numerical model.The suppression mechanism of rotor-stator interaction noise sources is explored to support the design of low-noise fans.

关 键 词：风扇单音噪声 转静干涉 非定常雷诺平均 三平面模态匹配 弯掠静子 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]