FIELD: mechanical engineering; gas-turbine engines.
SUBSTANCE: proposed three-circuit gas-turbine engine consists of two gas-turbine engines with common intake device. One of engines is shaft-turbine engine with free turbine being additional turbine for second engine. Second engine is ejector-turbine one. Both engines have common exhaust unit. Ratio of air flow rate through compressor of shaft-turbine engine and compressor of ejector-turbine engine at takeoff is 0.15-0.3.
EFFECT: improved combustion characteristics of ejector-turbine engine at subsonic speeds of flight.
3 dwg
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