A stator vane segment (SV) of an axial turbine, the stator vane segment (SV) comprising: three or more airfoil portions (AF); one outer band (OB) joined to a tip portion (TP) of each of the airfoil portions (AF); and one inner band (IB) joined to a hub portion (HB) of each of the airfoil portions (AF), wherein each of the airfoil portions (AF) is formed by stacking airfoil profiles in a spanwise direction from the hub portion (HB) to the tip portion (TP), and each of the profiles includes a leading edge (LE) and a trailing edge (TE), and a concave pressure surface (PS) and a convex suction surface (SS) each extending between the leading edge (LE) and the trailing edge (TE), in a stacking line (SL) obtained by connecting the respective trailing edges (TE) of the profiles at spanwise positions, a portion from the tip portion (TP) to a predetermined spanwise position (X) is a straight line parallel to a radial direction (R) of the axial turbine, a portion from the predetermined spanwise position (X) to the hub portion (HB) is shifted from the pressure surface (PS) toward the suction surface (SS) in a circumferential direction (C) of the turbine from the straight line parallel to the radial direction (R), and an amount of the shift monotonically increases from the predetermined spanwise position (X) to the hub portion (HB), and the amount of the shift in the hub portion (HB) of the airfoil portion (AF) having the suction surface (SS) located on an end side in the circumferential direction (C) of the stator vane segment (SV), of the three or more airfoil portions (AF), is larger than the amounts of the shift in the hub portions (HB) of other airfoil portions (AF) of the three or more airfoil portions (AF). three or more airfoil portions (AF); one outer band (OB) joined to a tip portion (TP) of each of the airfoil portions (AF); and one inner band (IB) joined to a hub portion (HB) of each of the airfoil portions (AF), wherein each of the airfoil portions (AF) is formed by stacking airfoil profiles in a spanwise direction from the hub portion (HB) to the tip portion (TP), and each of the profiles includes a leading edge (LE) and a trailing edge (TE), and a concave pressure surface (PS) and a convex suction surface (SS) each extending between the leading edge (LE) and the trailing edge (TE), in a stacking line (SL) obtained by connecting the respective trailing edges (TE) of the profiles at spanwise positions, a portion from the tip portion (TP) to a predetermined spanwise position (X) is a straight line parallel to a radial direction (R) of the axial turbine, a portion from the predetermined spanwise position (X) to the hub portion (HB) is shifted from the pressure surface (PS) toward the suction surface (SS) in a circumferential direction (C) of the turbine from the straight line parallel to the radial direction (R), and an amount of the shift monotonically increases from the predetermined spanwise position (X) to the hub portion (HB), and the amount of the shift in the hub portion (HB) of the airfoil portion (AF) having the suction surface (SS) located on an end side in the circumferential direction (C) of the stator vane segment (SV), of the three or more airfoil portions (AF), is larger than the amounts of the shift in the hub portions (HB) of other airfoil portions (AF) of the three or more airfoil portions (AF). <EOS>