FIELD: machine building.
SUBSTANCE: platform assembly to support the nozzle blade for the gas turbine contains gas passage surface, located such that to contact with flowing work gas, at least one cooling channel. The cooling channel has shape to direct the cooling fluid in the cooling channel, and is made inside the platform assembly. The cooling area of the internal surface of the cooling channel is in thermal contact with the gas passage surface. The platform assembly is integrally made assembly representing segment in circular direction of the gas turbine. The cooling channel contains the first area of the cooling channel, and the second area of the cooling channel, located after the first area of the cooling channel in relation to the flow direction of the work gas. The first area of the cooling channel, and the second area of the cooling channel are interrelated with each other such that the cooling fluid is directed to the first area of the cooling channel, and then to the second area of the cooling channel. The first area of the cooling channel, and the second area of the cooling channel mainly pass along the circle direction, and are suitable such that the first part of the cooling fluid flows in the first direction in the first segment of the first area of the cooling channel, and second part of the cooling fluid flows in the second direction in the second segment of the first area of the cooling channel, the first part of the cooling fluid flows in the first segment of the second area of the cooling channel, and the second part of the cooling fluid flows in the second segment of the second area of the cooling channel. The first part of the cooling fluid, and the second part of the cooling fluid flow towards each other, and combines in the second area of the cooling channel.
EFFECT: invention increases efficiency of cooling, and increases service life of the turbine nozzle blade.
14 cl, 3 dwg
