基于多种分析方法的低压涡轮边界层流动特性研究  

Study on flow characteristics of low-pressure turbine boundary layer based on multiple analysis methods

作　　者：孙爽[1] 黄禛 康晋辉 孙小鹏 王茂茂 卢乐晗 SUN Shuang;HUANG Zhen;KANG Jinhui;SUN Xiaopeng;WANG Maomao;LU Lehan(College of Aeronautical Engineering,CAUC,Tianjin 300300,China)

机构地区：[1]中国民航大学航空工程学院,天津300300

出　　处：《中国民航大学学报》2024年第5期36-44,共9页Journal of Civil Aviation University of China

基　　金：航空发动机及燃气轮机基础科学中心项目(P2022-B-Ⅱ-008-001)。

摘　　要：为探究航空发动机低压涡轮吸力面边界层受尾迹影响下的非定常流动特性,本文采用商用软件CFX 15.0进行数值模拟,并使用具有上游尾迹模拟功能的叶栅实验台进行了实验验证。首先,在保持轴向转速不变的情况下,调整上游尾迹杆转速实现了3种不同的上游尾迹折合频率。其次,利用数值模拟得到了3种工况下低压涡轮吸力面边界层流场数据并进行对比分析,分析中特别使用了本征正交分解(POD,proper orthogonal deco-mposition)、动态模态分解(DMD,dynamic mode decomposition)和傅里叶模态分解(FMD,Fourier mode decomposition)3种新式流场分析方法。结果表明,在3种折合频率下,尾迹中心通过分离区域时,其距离叶面的高度差别较大,尾迹作用下的吸力面边界层中尾迹的影响程度与识别到的主要特征也存在较大差别。To investigate the unsteady flow characteristics of the low-pressure turbine suction surface boundary layer of an aero-engine under the influence of wake,the commercial software CFX 15.0 was used for numerical simulation in this paper,and a cascade test platform with an upstream wake simulation function was used for experimental verification.Firstly,three different upstream reduced frequencies of wakes were achieved by changing the speed of the upstream wake bar while keeping the axial velocity unchanged.Then,by numerical simulation,the flow field data of the low-pressure turbine suction surface boundary layer under three conditions were obtained and compared.Three new flow field analysis methods including proper orthogonal decomposition(POD),dynamic mode decomposition(DMD)and Fourier mode decomposition(FMD),were used in the analysis.The results show that,under the three reduced frequencies,the height of the wake center from the blade surface differs greatly when it passes through the separation area.The influence degree of the wake in the suction surface boundary layer and the main identified characteristics are also very different under the influence of wake.

关 键 词：低压涡轮 边界层 尾迹 分离 卷升涡 

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]