The turbine stator blades and gas turbine

Turbine vane of the present invention includes an inner shroud that constitutes the outer shroud (8a) and an inner wall along a turbine circumferential direction constitutes an outer wall of the main channel together provided a plurality adjacent (8b), the inner shroud (8b) a blade body defining a flow of combustion gases toward the downstream side from the upstream side of the main channel to protrude from the surface of (8c), a retainer extending along and protruding from the rear surface of the inner shroud (8b) in the turbine circumferential direction (8d) When provided with a retainer (8d) is split gap minimum connecting the contacts of the inscribed circle inner shroud and the adjacent throat line (P) with the airfoil shape of the adjacent blade main body (8c) (8b) (K1 ) intersection of the (Q) is disposed on the downstream side of the.