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| Format: | Recurso digital |
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Zenodo
2026
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| Online Access: | https://doi.org/10.5281/zenodo.18245557 |
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Table of Contents:
- <p>In modern gas turbine compressors, achieving high efficiency and a wide stall margin is strongly hindered by the development of secondary flow structures in hub-casing corner regions and intense shock boundary layer interactions. The aerodynamic behavior of transonic axial compressors is typically categorized into three regimes: choke, peak efficiency , and near stall. Under choke conditions, a bow shock forms near the leading edge and a normal passage shock appears closer to the exit. At peak efficiency, these two shocks merge to create a characteristic delta shape on the suction side. Further throttling shifts the shock upward, eventually reaching the stability limit and triggering stall. Consequently, the operating range of the rotor is strongly dictated by shock structure, and one of the most effective design freedoms for influencing shock behavior is the application of 3D stacking techniques, namely blade sweep and lean.</p>