Effect of slot casing treatment on first stall stage of counter-rotating compressor

被引：0
作者：
Wang L. [1 ,2 ]
Gao L. [1 ,2 ]
Mao X. [1 ,2 ]
Guo Y. [1 ,2 ]
机构：
[1] School of Power and Energy, Northwestern Polytechnical University, Xi’an
[2] The National Key Laboratory of Aerodynamic Design and Research, Northwestern Polytechnical University, Xi’an
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2024年 / 39卷 / 06期
关键词：
compressor stall; counter-rotating; first stall stage; slot casing treatment; tip leakage flow;
D O I：
10.13224/j.cnki.jasp.20220392
中图分类号：
学科分类号：
摘要：
In order to explore the influence of slot casing treatment on the first stall stage of counter-rotating compressor， a two-stage counter-rotating compressor was taken as the research object. The influence of slot casing treatment on the first stall stage of the counter-rotating compressor was studied by numerical simulation method. The results showed that the slot casing treatment did not change the initial stall disturbance type of the counter-rotating compressor，which was still a spike stall. The first stall stage of the compressor was converted from rotor R2 to rotor R1 by the forward movement of the casing treatment， while the backward movement of the casing treatment did not change the stall stage of the compressor. After casing treatment， the leading edge spillage of the rotor R2 was inhibited， and the unsteady fluctuation intensity in the blade passage was reduced. However，the leading edge spillage of the rotor R1 was intensified under the near-stall condition. The interface between the mainstream and the leakage flow was pushed out of the blade passage. At the same time，the unsteady oscillation intensity in the blade passage was increased，which finally made the rotor R1 first enter the stall state. It was difficult to suppress the occurrence of leading edge spillage when the casing treatment was processed to move downstream of rotor R2. Although the leading edge spillage phenomenon also occurred at rotor R1 at this time，the leading edge spillage of rotor R2 was more intensified，and the position of the interface of the mainstream and leakage flow was further away from the leading edge of the blade，making it easier for the compressor to stall. © 2024 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.
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