FIELD: engines and pumps.
SUBSTANCE: proposed method consists in cooling air bled from engine and feeding it via bores made in turbine wheel into turbine vane inner spaces. Gas turbine engine represents a turbo ejector engine. Cooling air is bled from inlet device, cooled by mixing with water or fuel and forced into turbine vane inner spaces via engine shaft and bores of radial-flow compressor built in turbine wheel.
EFFECT: increased thrust power and flight speed due to higher temperature in main combustion chamber.
4 cl, 2 dwg
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