A turbine vane of the invention includes: a plurality of outer shrouds (8a) that are provided along the turbine circumferential direction so as to be adjacent to each other and form an outer wall of a main passageway; inner shrouds (8b) that form an inner wall; a airfoil body (8c) that protrudes from a front surface of the inner shroud (8b) and defines a flow of combustion gas directed from the upstream side of the main passageway toward the downstream side thereof; and a retainer (8d) which protrudes from a rear surface of the inner shroud (8b) and extends along the turbine circumferential direction, wherein the retainer (8d) is disposed on the downstream side in relation to an intersection point (Q) between a dividing gap (K1) of the adjacent inner shrouds (8b) and a throat line (P) which connects the contact points of a minimal inscribed circle according to the blade shapes of the adjacent airfoil bodies (8c).