International Journal of Gas Turbine, Propulsion and Power Systems
Online ISSN : 1882-5079
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  • Fanzhou Zhao, John Dodds, Mehdi Vahdati
    2021 Volume 12 Issue 2 Pages 1-7
    Published: 2021
    Released: April 10, 2021
    JOURNALS OPEN ACCESS
    This paper presents the interaction between blade vibration and part-span rotating stall in a multi-stage high speed compressor. Unsteady aerodynamic and aeroelastic simulations were conducted using URANS CFD. Steady state computations showed short length scale disturbances formed local to the tip of a front stage rotor. Using a full annulus model, these disturbances were shown to coalesce into flow structures rotating around the annulus at approximately 76% of the shaft rotational speed. Natural evolution of the rotating stall did not result in a coherent spatial pattern. Subsequent analyses carried out with prescribed rotor blade vibration showed a spatial ‘lock-in’ event where the circumferential order of the part-span rotating stall shifted to match that induced by the vibration mode. Moreover, in contrast to its natural form in the absence of vibration, the fully developed rotating stall showed a coherent stall signal.
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