Influence of inlet guide vane angle on flow instability of hub instability compressor

被引：0
|
作者：
Chen X. [1 ,2 ]
Wu W. [1 ,2 ]
Pan T. [1 ,2 ]
Li Q. [1 ,2 ,3 ]
机构：
[1] School of Energy and Power Engineering, Beihang University, Beijing
[2] Research Institute of Areo-Engine, Beihang University, Beijing
[3] Key Laboratory of Fluid and Power Machinery, Ministry of Education, Xihua University, Chengdu
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2023年 / 38卷 / 01期
关键词：
areo-compressor; flow instability; inlet pre-swirl angle; instability precursors; variable inlet guide vane;
D O I：
10.13224/j.cnki.jasp.20210355
中图分类号：
学科分类号：
摘要：
A high-speed aero-compressor with different instability precursors was taken as the research object. The inlet guide vane was installed to manipulate the compressor inlet pre-swirl angle. Several dynamic pressure transducers were arranged to measure the whole instability evolutions. The instability precursor and the evolutions were observed under different inlet guide vane angles. The results showed that at negative inlet guide vane angle， the compressor instability was caused by the spike in the rotor tip region. At zero inlet guide vane angle and small positive inlet guide vane angle， the instability was induced by the partial surge in the stator hub region. Under the condition of large positive inlet guide vane angle， local instability occurred at stator hub first in the process of throttling， and led to complete compressor instability with further throttling in form of rotating stall cells at the tip. The analysis showed that the increase of the inlet guide vane angle adjusted the load distribution between the rotor and the stator by reducing the degree of reaction， thus causing the instability precursors to change from “spike at rotor-partial surge at stator-local instability at stator” as described above. © 2023 BUAA Press. All rights reserved.
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页码：215 / 222
页数：7
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