A system and method for improving gas turbine perfomrance at part-load operation

A compressor section (12) of a gas turbine (10) generally includes a stage (30) of inlet guide vanes positioned adjacent to an inlet (14) of the compressor section and a stage (32) of rotor blades disposed downstream from the inlet guide vanes. A stage (34) of stator vanes is positioned downstream from the stage of rotor blades. The stage of stator blades includes a row (62) of leading guide vanes having a trailing edge. A row (64) of trailing guide vanes coupled to an actuator is disposed between two corresponding adjacent leading guide vanes. Each of the trailing guide vanes includes a trailing edge. The leading edge of each trailing guide vane is disposed upstream of the trailing edge of a corresponding leading guide vane when the trailing guide vane is in an open position and downstream from the trailing edge of the corresponding leading guide vane when the trailing guide vane is in a closed position.