Numerical investigation of the casing treatment mechanism with a single circumferential groove  

作　　者：SHI Ke CHEN HaiXin FU Song 

机构地区：[1]School of Aerospace,Tsinghua University

出　　处：《Science China(Physics,Mechanics & Astronomy)》2013年第2期353-365,共13页中国科学：物理学、力学、天文学（英文版）

基　　金：supported by the GE Aviation under its University Strategic Alliance(USA) program;supported by the National Natural Science Foundation of China(Grant Nos.10932005 and 11272183)

摘　　要：The paper investigates the effect of a single circumferential groove casing treatment(CGCT) on a transonic compressor rotor numerically.In particular,the effect of the groove at different axial locations on the flow field is studied in detail and stall margin improvement is also discussed.The present results show that the groove close to the leading edge plays a crucial role in stabilizing the near stall flow structures and,hence,improves the stall margin.The groove at the mid-chord-section of the blade can help exchange and transfer momentums between different directions,and suppress the flow unsteadiness,leading to increased efficiency in rotor performance and extended operation range.The groove located near the blade trailing edge has limited effects on stall margin improvement and may cause additional penalty in efficiency.Through comparison with the recent work on CGCT,some common flow physics can be observed.The paper investigates the effect of a single circumferential groove casing treatment （CGCT） on a transonic compressor rotor numerically. In particular, the effect of the groove at different axial locations on the flow field is studied in detail and stall margin improvement is also discussed. The present results show that the groove close to the leading edge plays a crucial role in stabilizing the near stall flow structures and, hence, improves the stall margin. The groove at the mid-chord-section of the blade can help exchange and transfer momentums between different directions, and suppress the flow unsteadiness, leading to increased efficiency in rotor performance and extended operation range. The groove located near the blade trailing edge has limited effects on stall margin improvement and may cause additional penalty in efficiency. Through comparison with the recent work on CGCT, some common flow physics can be observed.

关 键 词：compressor casing treatment circumferential groove transonic rotor stall margin 

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]