SYSTEM AND METHOD FOR IMPROVING GAS TURBINE PERFORMANCE AT PART-LOAD OPERATION

摘要

A compressor section of a gas turbine generally includes a stage of inlet guide vanes positioned adjacent to an inlet of the compressor section and a stage of rotor blades disposed downstream from the inlet guide vanes. A stage of stator vanes is positioned downstream from the stage of rotor blades. The stage of stator blades includes a row of leading guide vanes having a trailing edge. A row 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.