| Citation: | MA Shuai, WANG Zhiqiang, HU Jun. Experiment of the effect of steady distortion on the stability of an eccentric compressor[J]. Journal of Aerospace Power, 2025, 40（12）：20240696 doi: 10.13224/j.cnki.jasp.20240696
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In order to investigate the flow instability phenomenon in eccentric compressor and the effect of flow disturbance between inlet distortion and eccentricity on the aerodynamic instability of the compressor, experiments were carried out to measure the aerodynamic stability of a single-stage eccentric compressor under uniform inlet, four phases of steady-state circumferential total pressure distortion inlet and six phases of paired vortex flow distortion inlet. When the compressor was throttled to near-stall condition under uniform inlet, rotational instability occurred near the large clearance location, while the small clearance location was in an orderly steady flow. Further analysis revealed that the strongest region of unsteady flow in the eccentric compressor was about 45° after the largest clearance, which was very close to the region with the smallest flow coefficient. Experimental results under intake distortion showed that the phase relationship between intake distortion and eccentricity was a potential factor affecting the stability of the compressor. When the large incidence region induced by the circumferential total pressure distortion and the negative precession region induced by the vortex distortion were in the same phase as the region with the strongest flow instability under the uniform inlet of the eccentric compressor, the stability of the compressor decreased most seriously.
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