Abstract
An understanding of unsteady aerodynamic activity through blade passages of a turbine engine is essential to predict blade vibration. The unsteady aerodynamic pressures acting on the blade's surface make up the forcing function primarily contributing to blade vibration. This forcing function may stem from inlet distortions, viscous effects, boundary layer activity, shock-boundary layer interaction, separated flows, tip flows, and blade vibration. In the following effort, unsteady pressures acting on the blade surface of a transonic compressor are examined. Time and frequency domain analyses were used to analyze the transient behavior. The primary source of unsteady pressure in the following analysis was generated from an inlet distortion. The distortion was of engine order and narrow band. Ensemble averaging techniques were used to bring out the dominant effects of inlet distortion. On-blade pressure data were analyzed in terms of their spectral decomposition and phase. Finally, velocities were calculated from the phase data for tonal and broadband activity.
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