FIELD: gas-turbine engines.
SUBSTANCE: proposed cooled-two-stage turbine of gas-turbine engine with tubular or cannular combustion chambers contains nozzle box of first stage with cooled blades, turbine first stage impeller, and second stage nozzle box with cooled blades. Blades of first stage nozzle box, in number equal to number of flame tubes are arranged opposite to flame tube spaces. Blades of second stage nozzle box, in number equal to double number of flame tubes, are made with chord of profile defined by claim protected by invention. Blades of second stage nozzle box are displaced relative to two-row blades of first stage nozzle box with circular displacement defined by claim protected by invention. Manifold delivering cooling air to blades of second stage nozzle box is arranged in traces of two-row blades of first stage nozzle box and is provided with throttle cock.
EFFECT: reduced consumption of coolant (air), increased efficiency of cooled two stage turbine of gas-turbine engine.
7 dwg
