Axial flow compressor, gas turbine including the same, and stator blade of axial flow compressor

An axial flow compressor comprising:

• multiple rotor blade rows configured to include multiple rotor blades and multiple stator blade rows configured to include multiple stator blades, the multiple rotor blades and the multiple stator blades being arranged inside an annular channel through which a working fluid flows,
• wherein a first portion of at least one wall surface on an inner peripheral side and an outer peripheral side of the annular channel has a protruding portion such that downstream side part of the first portion is curved so as to further protrude to the annular channel than upstream side part of the first portion, where the first portion is disposed in a place where at least one of the rotor blade rows and the stator blade rows is located, and
• wherein each of the multiple rotor and stator blades located at the protruding portion of the wall surface is configured such that a blade outlet angle in a blade height portion monotonously changes toward the wall surface having the protruding portion and an increase rate of a blade outlet angle at a blade end on a side of the wall surface having the protruding portion is greater than an increase rate of the blade outlet angle in the blade height portion.