TURBINE VANE AND GAS TURBINE
A turbine vane of the invention includes: a plurality of outer shrouds ( 8 a ) 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 ( 8 b ) that form an inner wall; a airfoil body ( 8 c ) that protrudes from a front surface of the inner shroud ( 8 b ) and defines a flow of combustion gas directed from the upstream side of the main passageway toward the downstream side thereof; and a retainer ( 8 d ) which protrudes from a rear surface of the inner shroud ( 8 b ) and extends along the turbine circumferential direction, wherein the retainer ( 8 d) is disposed on the downstream side in relation to an intersection point (Q) between a dividing gap (K 1 ) of the adjacent inner shrouds ( 8 b ) 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 ( 8 c ).
1 . A turbine vane comprising:
a plurality of outer shrouds 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;
a plurality of inner shrouds that are provided along the turbine circumferential direction so as to be adjacent to each other and form an inner wall of the main passageway;
a airfoil body that protrudes from a front surface of the inner shroud and defines a flow of combustion gas directed from the upstream side of the main passageway toward the downstream side thereof; and
a retainer that protrudes from a rear surface of the inner shroud and extends along the turbine circumferential direction,
wherein the retainer is disposed on the downstream side in relation to an intersection point between a dividing gap of the adjacent inner shrouds in the turbine circumferential direction and a throat line which connects contact points formed between the airfoil bodies and a minimal inscribed circle formed between the adjacent airfoil bodies in the turbine circumferential direction.
2 . The turbine vane according to claim 1 ,
wherein the retainer is fixed to the turbine body through a support ring with which the downstream-side surface thereof comes into contact, and a sealing member is provided between the retainer and the support ring.
3 . A gas turbine comprising:
the turbine vane according to claim 1 .