The performance of a modern, forward-swept, transonic compressor rotor has been characterized operating behind an inlet-guide (IGV) vane section that has variable flaps. Testing was performed at both transonic and subsonic rotor tip speeds in an attempt to determine the off-design performance of the rotor at various flap angle settings of the IGV’s. Measurements at moderate flap angles (+20° and −10°) have been determined up to 90% speed (27,000 rpm) of the drive turbine maximum capability. Extremely high flap angles, in excess of +55°, were tested down into the low speed range. For this study the negative flap angles produced counterswirl and the positive flap angles produced swirl in the same direction as the rotation of the rotor.

A rigorous definition of the mass-averaged efficiency is presented. Performance predictions were carried out using ANSYS-CFX on a single passage model consisting of both the IGV and the rotor. Reasonable comparisons with a medium mesh resolution were obatined when compared to experiment.

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