FIELD: machine building.
SUBSTANCE: high temperature gas turbine comprises a labyrinth seal as per honeycomb block on the inner shoulder made with a baffle plate and with an internal air cavity of the nozzle blade being cooled. The air cavity at the nozzle blade outlet is connected to the perforation which leads to internal cavities of honeycomb block cells via a dosing hole in the baffle plate and via a distributing channel and axial channel system which are set in the inner shoulder circumferentially. The axial channels are additionally connected by perforation to the outer surface of the inner shoulder of the nozzle blade.
EFFECT: invention improves reliability and cost efficiency of a high temperature gas turbine due to the prevention of overheating and destruction of the honeycomb block of a labyrinth seal, and reduction of the radial clearance in the seal.
2 cl, 3 dwg
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