Numerical Investigation of Circumferential Groove Casing Treatment in a Highly-Loaded Low-Reaction Transonic Compressor Rotor  

作　　者：ZHU Wei CAI Le WANG Songtao WANG Zhongqi 

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

出　　处：《Journal of Thermal Science》2020年第4期916-927,共12页热科学学报（英文版）

基　　金：support of the National Natural Science Foundation of China(NSFC),Grant No.51706052。

摘　　要：In this paper, a computational investigation of circumferential groove casing treatment in a highly-loaded low-reaction transonic compressor rotor is conducted, in which the stage reaction is significantly reduced due to a larger meridional contraction with respect to conventional transonic compressors. Steady computation at near-stall point is performed first to capture the stall inception of the rotor with smooth casing. Detailed observations, which mainly focus on the tip leakage flow behavior, obstruction and vortical structures in the tip region, determine the reason for the compressor stall. There is tip leakage vortex breakdown in the tip region. Moreover, it yields passage obstruction, and finally leads to the compressor stall. Then, attempts are made to investigate how the circumferential grooves can be applied for the compressor’s stall margin enhancement without compromising efficiency. Three configurations are obtained and analyzed by changing axial position and the number of the circumferential grooves. The results of computational parametric study indicate the optimal location of the groove is near the leading edge and the downstream grooves combine their influence on the compressor’s stabilization and performance in a cumulative manner. The optimal circumferential groove configuration produces an increase of 1% in total pressure ratio at the near-stall point and a gain of 3.7% in stall margin, without any penalty in efficiency. Furthermore, the impact the grooves will exert on the flow mechanisms between the grooves and the main flow is also considered.

关 键 词：low-reaction transonic compressor circumferential casing groove vortex breakdown stall margin 

分 类 号：V233[航空宇航科学与技术—航空宇航推进理论与工程] TK474.81[动力工程及工程热物理—动力机械及工程]