HIGH TEMPERATURE GAS TURBINE Russian patent published in 2014 - IPC F02C7/12 

FIELD: machine building.

SUBSTANCE: first nozzle blade by its upper flange is installed in the outer casing of the combustion chamber, and by the radial ribs of the lower flange it is installed in the grooves of the inner ring of the first nozzle diaphragm. The inner ring is made with a resilient member of U-shaped cross section with the central part of the resilient member being fastened to the support of the nozzle diaphragm. The inner ring part being the front one in the downstream gas direction is provided with the channels for the supply of cooling air to the nozzle blade. The inner ring part being the rear one in the downstream direction is provided with the annular axial rib of a labyrinth seal along the lower flange of the first working blade. The angle of inclination of the annular rib's inner surface to the turbine axis falls within 20-40°. The ratio of the height of the resilient member's radial wall to the thickness of the resilient member's radial wall falls within the range of 6-10.

EFFECT: invention decreases the stress in the first nozzle blade and decreases the temperature of the lower flange of the first nozzle blade thus improving the reliability of a high temperature gas turbine.

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