One-stage stator vane cooling structure and gas turbine
View Patent ↗A one-stage stator vane cooling structure consisting of: a plurality of linking members that are provided between a plurality of combustors disposed in the circumferential direction of a gas turbine; and cooling holes that are provided in each of the one-stage stator vanes to discharge a cooling gas from the inside to the outside of the one-stage stator vanes in order to cool the one-stage stator vanes on the periphery of the stagnation line of the combustion gas flowing in from the plurality of combustors; in which the cooling holes are formed at positions that are determined according to the relative positions of the one-stage stator vanes and the linking members disposed near the one-stage stator vanes.
1. A one-stage stator vane cooling structure comprising:
a plurality of linking members that are provided between a plurality of combustors disposed in a circumferential direction of a gas turbine; and
cooling holes that are provided in each one-stage stator vanes to discharge a cooling gas from an inside to an outside of the one-stage stator vanes in order to cool a stagnation line formed on or near a leading edge of the one-stage stator vanes by means of stagnation of combustion gas flowing in from the plurality of combustors,
wherein the cooling holes are formed at positions that are determined according to relative positions of the one-stage stator vanes and the linking members disposed in a vicinity of the one-stage stator vanes,
wherein a pressure surface side of the one-stage stator vanes has a concave surface between the leading edge and a trailing edge,
wherein the plurality of linking members are arranged with a mutually equal interval in a circumferential direction of the gas turbine,
wherein the one-stage stator vanes of a number that is an integer multiple of a number of the combustors are arranged with a mutually equal interval in the circumferential direction of the gas turbine, and
wherein the one-stage stator vanes that are closest in the circumferential direction of the gas turbine to the linking members are disposed so that a relative position ratio S/P that is a ratio of S to P becomes greater than or equal to −10% and less than or equal to +30%, where P and S are as follows:
P: a pitch of a distance between two successive one-stage stator vanes in the circumferential direction of the gas turbine, and
S: a distance in the circumferential direction of the gas turbine of a center position of the linking member in the circumferential direction that is in a vicinity with respect to the leading edge of the one-stage stator vane, the distance being a negative value in a case of the linking member that is in the vicinity shifting to a dorsal side of the one-stage stator vane, and a positive value in the case of the linking member that is in the vicinity shifting to a ventral side of the one-stage stator vane.
2. A gas turbine comprising:
a compressor that generates compressed air;
a turbine that has a stator vane and a rotor vane of at least one stage each, and generates rotative power by combustion gas; and
a plurality of combustors that are disposed in a circumferential direction of the turbine, linked by a plurality of linking members that are provided in spaces therebetween, and that supply to the turbine combustion gas that is generated by supplying fuel to the compressed air that is supplied from the compressor,
wherein the one-stage stator vane cooling structure according to claim 1 is provided in the one-stage stator vane that is positioned most to the combustor side among the stator vanes of the turbine.