Abstract
A series of experiments to investigate rotor unsteady aerodynamic response to high and very high reduced frequency gusts, including the effects of steady aerodynamic loading and detailed forcing function waveform shape are described. These experiments are performed in an extensively instrumented axial flow research compressor. The high reduced frequency forcing function to the first stage rotor blade row is the first harmonic of the wakes generated by the 36 inlet guide vanes (IGV’s), with the very high reduced frequency being the second harmonic of these wakes. These forcing functions are each measured in the rotor frame of reference, decomposed into chordwise and transverse velocity components, and then Fourier analyzed. The unsteady aerodynamic gust response is then investigated on the individual surfaces of the first stage rotor blade for two values of the streamwise-to-transverse gust amplitude ratio over a range of compressor steady loadings. Appropriate data are correlated with classical predictions. The results show that there are large and significant differences between the high and very high reduced frequency gust generated unsteady aerodynamic response of the rotor blade row.
Published Version
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