Abstract
A mathematical model is developed to analyze vane row indexing for passive e ow-induced vibration control. A compressible e at-plate cascade analysis is extended to account for the induced velocities due to the potential e elds of adjacent blade rows. Then, this model is applied to a baseline stator ‐rotor‐stator cone guration with the effects of Mach number, steady vane loading, and axial spacing investigated. For the particular geometry analyzed, the minimum unsteady lift and maximum unsteady moment responses occur near the unindexed position of the stator vane rows; simply decreasing the axial spacing markedly affects the rotor-blade unsteady aerodynamic response. However, by indexing the stator vanes, signie cant reductions in the unsteady lift and moment are achieved at the close spacings. At the closest spacing, near complete cancellation of the unsteady lift is possible at low Mach numbers. At high Mach numbers, there are optimum combinations of upstream and downstream rotor ‐stator axial spacings, which can result in complete cancellation of the unsteady lift, with signie cant reductions in the unsteady lift possible even for a moderate axial spacing of 30% chord.
Published Version
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