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Stall mechanisms in multi-stage axial compressors at different rotational speeds and identification of initial stall locations

Published online by Cambridge University Press:  14 November 2025

X. Yang Open the ORCID record for X. Yang [Opens in a new window] ,
W. Chu Open the ORCID record for W. Chu [Opens in a new window] ,
H. Zhang ,
L. Huang ,
Q. Li  and
H. Wang Open the ORCID record for H. Wang [Opens in a new window]
X. Yang
Affiliation:
National Elite Institute of Engineering, Northwestern Polytechnical University, Xi’an, China
W. Chu*
Affiliation:
National Elite Institute of Engineering, Northwestern Polytechnical University, Xi’an, China School of Power and Energy, Northwestern Polytechnical University, Xi’an, China
H. Zhang
Affiliation:
National Elite Institute of Engineering, Northwestern Polytechnical University, Xi’an, China School of Power and Energy, Northwestern Polytechnical University, Xi’an, China
L. Huang
Affiliation:
School of Power and Energy, Northwestern Polytechnical University, Xi’an, China AECC Sichuan Gas Turbine Establishment, Chengdu, China
Q. Li
Affiliation:
School of Power and Energy, Northwestern Polytechnical University, Xi’an, China
H. Wang
Affiliation:
School of Power and Energy, Northwestern Polytechnical University, Xi’an, China
*
Corresponding author: Wuli Chu; Email: wlchu@nwpu.edu.cn
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Abstract

To investigate the stall mechanisms of a multi-stage axial compressor under different rotational speeds and identify the initial stall stages, this study focuses on a high-load nine-stage axial compressor, validated through experimental data. The results reveal that at 100% corrected rotational speed, flow instability is primarily triggered by corner separation in the front four stators (S1–S4). At 80% corrected rotational speed, the instability stems from the interaction between the first rotor (R1) tip leakage vortex and the main flow, coupled with the front four stators’ corner separation. Precise identification of initial stall locations in multi-stage axial compressors is imperative. The study first employs qualitative flow-field analysis to identify initial stall locations by comparing meridional mass flux variation contour maps and axial velocity iso-surfaces. The results show that the stall inception occurs at the S2 root under 100% corrected rotational speed, while at 80% corrected rotational speed, stall initiates simultaneously at both the S2 root and the R1 tip. Furthermore, an innovative three-dimensional flow blockage quantification method was established to systematically evaluate blockage severity within multi-stage blade passages. This approach utilises relative blockage variation metrics to quantitatively identify regions of rapid flow deterioration, achieving remarkable consistency with qualitative flow-field analysis. The qualitative and quantitative analysis results have been mutually corroborated. The proposed blockage quantification approach enables precise evaluation across stages without complex flow fields comparisons, allowing rapid identification of stall-initiating locations and supporting subsequent stability enhancement optimization.

Keywords

blockage quantificationcompressor stabilityinitial stall locationsmulti-stage compressorstall mechanism

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 130 , Issue 1345 , March 2026 , pp. 944 - 964
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Copyright
© The Author(s), 2025. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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