AXIAL FLOW COMPRESSOR, GAS TURBINE SYSTEM HAVING THE AXIAL FLOW COMPRESSOR AND METHOD OF MODIFYING THE AXIAL FLOW COMPRESSOR

摘要

PROBLEM TO BE SOLVED: To provide an axial flow compressor that improves reliability on an increase in a blade loading on a last-stage stator vane of the axial flow compressor due to a partial load operation of a gas turbine and the like.SOLUTION: An annular flow passage is formed by a rotor to which multiple rotor blade cascades are attached and a casing to which multiple stator vane cascades are attached. Two or more of the stator vane cascades are disposed at the downstream side of a last-stage rotor blade cascade that is the rotor blade cascade disposed at the most downstream side in a flow direction of the annular flow passage. In addition, a blade loading on a first stator vane cascade disposed at the most upstream side is set to be smaller than a blade loading of a second stator vane cascade disposed at the downstream side of the first stator vane cascade by one row, at the stator vane cascade disposed at the downstream side of the last-stage rotor blade cascade.