<p class="MsoBodyTextIndent"><i>The blade row interactions, including stator-stator, rotor-rotor, and rotor-stator interactions can impact stage aerodynamic performance and rotor resonant response. Interactions of the wakes from upstream blade rows and the potential field from both upstream and downstream blade rows yield complex nonuniform circumferential flow in compressors. Much efforts have been put to understand the blade row interactions in multi-stage axial compressors. In the present paper, the full annuls nonuniform circumferential flow field downstream of Stator 1, Rotor 2, and Stator 2 are reconstructed to assist in better understanding of blade row interactions between Stator 1 and 2. The study was conducted in the Purdue 3-Stage (P3S) Axial Compressor Research Facility using the PAX100 compressor with a reduced vane count for stator 1 (denoted PAX101). In the experiment, seven-element total pressure rakes were placed behind Stator 1, Rotor 2, and Stator 2 at three different circumferential. A thorough test campaign was carried out to map an approximate 1/6 of the full annulus, and the full-annulus total pressure field is reconstructed from a small segment of data representing 20% coverage of the annulus using a novel multi-wavelet approximation method. Both magnitude and phase information of the dominant wavelets were characterized. The features associated with blade-row interactions accounting for passage-to-passage variations are resolved in the reconstructed total pressure profile. Discussions regarding the blade row interactions in a multi-stage environment are presented. </i></p>

Understanding the Blade Row Interactions in a Multi-Stage Axial Compressor From the Circumferentially Reconstructed Flow Field

Paper Proceedings: https://asmedigitalcollection.asme.org/GT/GT2021/volume/84898

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