Flow Analysis of Tandem Blades as the Outlet Vane of a Highly Loaded Compressor  

作　　者：LUO Qiao LUO Lei DU Wei YAN Han WANG Songtao ZHOU Xun 

机构地区：[1]School of Energy Science and Engineering,Harbin Institute of Technology,Heilongjiang 150001,China

出　　处：《Journal of Thermal Science》2024年第6期2005-2018,共14页热科学学报（英文版）

基　　金：supported by the National Science and Technology Major Project (Nos.2017-Ⅱ-0007-0021 and P2021-AB-I-003-001);the Heilongjiang Province Postdoctoral Special Funding (LBH-TZ2109)

摘　　要：A tandem blade configuration is a significant flow control method that delays the onset of flow separation.This study numerically investigates the effects of diffusion factor and percentage pitch on the flow structure of tandem blades.Diffusion factors vary from 0.328 to 0.484.Percentage pitches change from 0.80 to 0.92.Results show that the loss coefficient increases with diffusion factor and decreases with percentage pitch.There is a hub-corner stall of the forward blade in all cases.Gap flow determines the rear blade corner separation.Varying the percentage pitch and diffusion factor changes the momentum distribution of the gap flow.Corner separation of the rear blade is inhibited as low-momentum gap fluids are involved in the passage vortex along with the hub-corner stall of the forward blade.Increasing diffusion factor causes a change in incidence at the leading edge of the rear blade,resulting in a variation at the corner separation of the rear blade.A tandem blade is compared with the reference outlet vane.The performance of the tandem blade is superior to that of the reference outlet vane in all incidences,with a 26.35%reduction in the loss coefficient and a 7.89%enhancement in the pressurization at the designed incidence.Tandem blades stall at positive incidence because of the hub-corner stall of the forward blade.The intensity of the gap flow increases with incidence,preventing corner separation of the rear blade at positive incidences.

关 键 词：COMPRESSOR tandem blade loss corner separation gap flow 

分 类 号：TK471[动力工程及工程热物理—动力机械及工程] V231[航空宇航科学与技术—航空宇航推进理论与工程]