The aeroelastic effects during stall inception in modern axial compressor are yet to be fully understood. Experimental investigations of two rotor designs, conducted at the 1.5-stage transonic compressor test rig at TU Darmstadt, using extensive unsteady aerodynamic and structural instrumentation, show global trends and influencing parameters on non-synchronous vibration and associated unsteady aerodynamics.  
During transient operation at transonic and subsonic speed, the pre-stall disturbances, as characterized by unsteady wall pressure transducers, vary in count, size, cell propagation speed and trajectory. The interaction with 1T-NSV, captured by strain gauges and blade tip timing, results in changing stability mechanisms, indicating influences of pre-swirl, rotor speed and blade count on the traveling aerodynamic wave as well as the coupling with the structural wave. Supplementary numerical simulations of the test setup extend the available set of aerodynamic and aeromechanical data, emphasizing the observed global trends and influencing parameters.  
The results indicate that different coupling conditions are evident, depending on the time scales of the convective motion of aerodynamic cells relative to the blade pitch. Ultimately, the excitation of a particular blade eigenmode and corresponding aeroelastic coupling with respect to varying compressor operation conditions is described. Thus, this paper contributes to the understanding of non-synchronous vibration and unsteady aerodynamics as well as corresponding coupling mechanisms.


Influence of Pre-Swirl, Rotor Speed and Blade Count on Aeroelastic Coupling Mechanisms During Stall Inception of a Transonic Compressor

Division / Sponsor:
International Gas Turbine Institute (IGTI)

Paper Proceedings: https://asmedigitalcollection.asme.org/GT/GT2020/volume/84058

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