AXIAL FLOW COMPRESSOR, GAS TURBINE INCLUDING THE SAME, AND STATOR BLADE OF AXIAL FLOW COMPRESSOR

摘要

An axial flow compressor 1 includes multiple rotor blade rows 12 configured to include multiple rotor blades and multiple stator blade rows 14 configured to include multiple stator blades, the multiple rotor blades and the multiple stator blades being arranged in an annular channel P through which a working fluid flows. Aportion of at least one wall surface on an inner peripheral side and an outer peripheral side of the annular channel P, the portion being at an arrangement portion where at least any one blade row of the rotor blade rows 12 and the stator blade rows 14 is located, has a protruding portion 24 such that downstream side part of the portion is curved so as to further protrude to the annular channel P than upstream side part of the portion. Each blade of the blade row 14 located at the protruding portion 24 of the wall surface 23 is configured such that an increase rate in a wall surface direction of a blade outlet angle in a blade end portion on the side of the wall surface 23 having the protruding portion 24 is greater than an increase rate in the wall surface direction of a blade outlet angle in a blade height intermediate portion.