Abstract
A series of experiments are described that are directed at the quantitative investigation of turbomachine rotor blade row unsteady unresolved velocities and blade surface pressures generated by the wakes from upstream blade and vane airfoil rows. The ensemble-averaged velocities and pressures quantify the vane wake generated periodic and aperiodic unsteadiness, with the unresolved unsteadiness defined by the variance. The vane wake generated aperiodic, periodic, and unresolved axial and tangential unsteady velocities and correlations are quantified at the inlet to each rotor row of a three-stage axial flow research compressor by means of a rotating cross hot-wire probe. The rotor blade surface unresolved unsteady pressure—time distributions and time-averaged values are also quantified for each rotor row, accomplished by means of ultraminiature high-response pressure tranducers.
Published Version
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