FIELD: engines and pumps.
SUBSTANCE: proposed gas turbine engine features turbine first-stage nozzle vanes arranged on combustion chamber gas collector outlet. Gas collector inner wall rear part is perforated and arranged on first-stage nozzle vane outer part. Its is limited by front and rear circular grooves arranged to receive nozzle vane radial ledges. U-like section compensator is arranged between perforated wall and read circular groove. Perforated wall outer surface is made equidistant from cooled surface of first-stage nozzle vane lower shelf.
EFFECT: higher reliability.
2 dwg
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