International Journal of Gas Turbine, Propulsion and Power Systems
Online ISSN : 1882-5079
  • Fanzhou Zhao, John Dodds, Mehdi Vahdati
    2021 年 12 巻 2 号 p. 1-7
    発行日: 2021年
    公開日: 2021/04/10
    ジャーナル オープンアクセス
    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.