| Citation: | YAO Zihang, WANG Hao, SUN Binhe, et al. Circumferential non-uniform flow characteristics and stall criterion of eccentric compressors[J]. Journal of Aerospace Power, 2025, 40（9）：20240354 doi: 10.13224/j.cnki.jasp.20240354
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Under actual operating conditions of compressor, factors such as shaft eccentricity, casing deformation or machining and assembly errors may lead to circumferential non-uniform characteristics of blade tip clearance, yielding an important impact on its performance, especially its stability. Taking NASA Rotor 67 as the research object, the circumferential non-uniform conditions caused by shaft eccentricity were studied numerically. The circumferential non-uniform distribution conditions of tip clearance were established by means of casing-rotor separated-domain modeling, and the three-dimensional compressor flow field under three eccentricity conditions was simulated to obtain the circumferential non-uniform distribution rules of flow field, and the stall criteria of compressor with circumferential non-uniform clearance were established based on the ‘equivalent clearance principle’. The results showed that the increase of tip leakage flow in the large clearance area of the eccentric rotor led to the intensified blocking effect, and the local tip flow coefficient decreased and got closer to the stall boundary, while the small clearance area was opposite. The extremum position of flow coefficient did not coincide with that of gap and had a certain phase delay. The stalling flow coefficient of the eccentric rotor was close to that of the concentric rotor with the average clearance of large gap sectors. Therefore, the equivalent principle of ‘average clearance of large gap sectors’ can be used as the criterion for estimating the stalling point of the circumferential non-uniform gap compressor.
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