Experimental and numerical investigation of two blended blade and endwall configurations  

作　　者：Tongtong MENG Xin LI Ling ZHOU Lucheng JI 

机构地区：[1]Institute for Aero Engine,Tsinghua University,Beijing 100084,China [2]Schoolof Aerospace Engineering,Bejing Institute of Technology,Beijing 0081,China

出　　处：《Chinese Journal of Aeronautics》2024年第9期150-163,共14页中国航空学报（英文版）

基　　金：co-supported by the National Major Science and Technology Project of China(No.2019-Ⅱ-0003-0023)

摘　　要：The Blended Blade and Endwall(BBEW)technique has proven to be effective in control-ling the intersection of boundary layer in corner region of the compressor endwall.In this study,the experiment and analysis of two different BBEW designs are emphasized.First,based on a linear cas-cade with 0.7 Mach number inflow,two different configurations,BBEW 1 and BBEW 2,are well conducted.Then,according to the experimental result,control effects of these two BBEW configu-rations are validated and compared subsequently under various working conditions.The results demonstrate a reduction in total pressure loss of 12.8%and 29%at the design point for BBEW 1 and BBEW 2,respectively.Consequently,the BBEW technique proves effective in suppressing the development of the boundary layer and preventing corner separation.Followed by detailed numerical analysis,improvements around the corner region,especially for the boundary layer,are extracted to show the mechanisms and distinctions between the two configurations.The results indicate that BBEW 1 significantly restrains the development of boundary layer before separation occurs,while BBEW 2 directly controls the strength and scale of the corner separation.

关 键 词：Aerodynamic Computational fluid dynamic Experiment Corner separation Blended Blade and Endwall(BBEW) 

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]