Experiment investigation on the effect of inlet circumferential non-uniformity on the stall behaviours in a transonic axial compressor with axisymmetric stall precursor
Author:
Publisher
Elsevier BV
Subject
Aerospace Engineering
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1. Partial tip air injection to extend the stall margin in an axial flow compressor with circumferential inlet distortion;Aerospace Science and Technology;2024-01
2. Experimental analysis of performance and tip dynamic pressure in a compressor cascade with high-speed moving endwall;International Journal of Turbo & Jet-Engines;2023-06-27
3. An Experimental Facility with the High-Speed Moving Endwall for Axial Compressor Leakage Flow Research;Aerospace;2023-02-25
4. Stall identification methods in centrifugal compressor;MATEC Web of Conferences;2023
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