FIELD: engines and pumps.
SUBSTANCE: proposed gas turbine engine comprises high-pressure compressor and combustion chamber with elastic shells. Compressor outer casing is separated from combustion chamber diffuser. Compressor straightener blades are fitted on two elastic shells of combustion chamber diffuser. Said blades have their top shrouds fitted through diffuser elastic shell circular grooves. Blade bottom shrouds are secured on combustion chamber diffuser outer elastic shell. Diffuser inner elastic shell is provided with labyrinth seal flange to make closed chamber between seal and blade bottom shrouds. Said flange is secured by nuts inside said chamber.
EFFECT: higher reliability.
2 cl, 3 dwg
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