SEGMENT platform designed for supporting the guide vanes of the nozzle guide vanes, AND METHOD FOR COOLING OF SEGMENT

摘要

1. Segment platform adapted for supporting the nozzle guide vane for a gas turbine, wherein the platform section comprises: - a surface (117, 119) of the channel for the passage of gas arranged so that it is in contact with the gas flow exiting from the chamber combustion, wherein the gas flow channel extends along the surface of the gas passage in the direction (101) of the flow - the surface (131, 149) cooling channel disposed opposite the surface for the gas passage and having a thermal coupling with the surface of the channel for the passage of gas And arranged so that it is in contact with the cooling fluid, - a wall (133, 151) projecting from the cooling surface and extending at least partially in the direction (101) of the flow, wherein the wall is located in the circumferential direction between the locations , which should be provided adjacent vanes, so that the cooling fluid will be directed through channels for the passage through this wall for cooling of the downstream portion of the cooling surface; u additional wall (133, 151) projecting from the cooling surface and extending at least partially in the direction (101) of the flow, the distance in the circumferential direction between the wall and the additional wall decreases along the direction (101) of the flow, wherein the nozzle guide vane having a pressure surface and a suction surface configured to couple to a segment platformytak that the pressure surface segment and the platform form a first edge along the first curved line where a surface and detecting and Segment